Delta Credit - (c) Mark Wade

Orbital launch vehicle. Country: USA. Status: Active.

The Delta launch vehicle was America's longest-lived, most reliable, and lowest-cost space launch vehicle. Delta began as Thor, a crash December 1955 program to produce an intermediate range ballistic missile using existing components, which flew thirteen months after go-ahead. Fifteen months after that, a space launch version flew, using an existing upper stage. The addition of solid rocket boosters allowed the Thor core and Able/Delta upper stages to be stretched. Costs were kept down by using first and second-stage rocket engines surplus to the Apollo program in the 1970's. Continuous introduction of new 'existing' technology over the years resulted in an incredible evolution - the payload into a geosynchronous transfer orbit increasing from 68 kg in 1962 to 3810 kg by 2002. Delta survived innumerable attempts to kill the program and replace it with 'more rationale' alternatives. By 2008 nearly 1,000 boosters had flown over a fifty-year career, and cancellation was again announced.

The Delta space launch family had its roots in the Thor IRBM. Thor was a 2400 km range missile with essentially the same characteristics as the Army's Jupiter. It was developed by Douglas Aircraft in one of the most accelerated crash programs in history. 'Chief Designer' of the Thor was Jack Bromberg. He was not educated formally as an engineer, but was smart and dynamic. Company owner Donald Douglas had hired him back in the 1930's. He was a major influence in Douglas' winning response to the USAF request for proposal, which emanated from USAF Missile Czar General Bernard Schriever.

The Air Force requirement was to build an IRBM around a discarded rocket motor design. The engine had been developed as the sustainer engine for the Atlas missile when the requirement was to launch a 2700 kg thermonuclear warhead over an intercontinental range. When it became apparent that the warhead could be reduced to less than half that weight, the Atlas was downsized, and the 68 tonne thrust sustainer motor was no longer required.

Douglas flew a first prototype only thirteen months after go-ahead. Sixty Thors were deployed to missile sites in Great Britain under Project Emily. After a few years the Thors were withdrawn from Britain (and the Jupiters from Turkey) as part of the secret codicil of Kennedy's deal to end the Cuban Missile Crisis. A few continued in an offensive military role as a nuclear-tipped anti-satellite system, based on Johnson Atoll in the Pacific, until the end of the early 1970's. Surplus Thors were used for a variety of suborbital re-entry vehicle tests.

After the Sputnik shock, all available assets were pressed into service. Thor was developed into a workhorse for the space program. The Able stage developed for the Vanguard project was mated to the Thor. A fundamental problem was that the thrust to weight ratio of the basic vehicle left little margin for growth or larger upper stages. This was solved by using Castor solid rockets strapped to the base of the vehicle to increase the lift-off thrust. Almost by accident rather than design, Thor developed into the Delta, the standard American medium-lift launcher, continually evolving through the use of more and larger strap-on boosters, a cylindrical and stretched core, and enlarged upper stages. The original Aerojet Able upper stage evolved into the Delta. From 1959-1972 the US Air Force and NASA flew versions of the launch vehicle using the same core and solid booster technology, but with the Agena upper stage rather than the Delta. After going through a bewildering myriad of military versions it emerged as the standardized, reliable and economical Delta commercial satellite launch vehicle by the mid-1970's. Improved Delta versions continued in production into the next millennium, with nearly 1,000 airframes completed, and the end of production announced yet again in 2008.

The innumerable 'deaths' and resurrections of the Delta are described in Aerojet - The Creative Company, 1995:

Using NASA terminology, their first Delta launch vehicle was basically an Air Force Able consisting of a Thor first stage, an Able second stage, and a solid propellant third stage of nominally 2760 lbf thrust produced by Allegheny Ballistics Laboratory (ABL). These vehicles and their powerplants are discussed above as part of the Able family. The first NASA contracts for these upper stages were in 1959, deliveries began in 1961, and numerous additional contracts followed. Also in 1961, NASA shifted to the Ablestar configuration. The first launch using this configuration occurred on May 13, 1960 and, according to one source on NASA history, did not reach orbit because of a malfunction in the Aerojet stage. Aerojet's findings indicate that it never got the signal to fire. The second attempt on August 12, 1960 was successful, and these engines were used until years later when the more powerful Air Force Delta second stage ablative engines became available.

At this point the Air Force, realizing the need for a larger space launch capability separate from the civilian efforts, selected the concept of using both stages of Titan II with various third and fourth stages, and later an array of zero stages. In very general terms, they retained the Agena for Thor and Atlas upper stages, and sought a new larger and simpler third stage, which was called Transtage. Agena was, however, regularly used on both Thor and Titan lower stages, and was often favored because it was a pump fed unit and was much lighter. The desirability of low chamber pressure, ablative chambers and a pressurized propellant feed system had been demonstrated in Vanguard, Hydra, and Ablestar, which led to the selection (for Titan) of the Transtage configuration using two chambers similar to, but larger than Ablestar. A variation of this became known as the Improved Delta stage, and was used extensively on Thor -so much so that the vehicle became known as Thor/Delta, and in some cases, only as Delta, or later as Thrust Augmented Delta, Long Tank Delta, Delta - PAM, and similar versions.

The resulting (improved) Delta launch vehicle underwent a bewildering succession of changes in configuration and performance (some incremental and some extensive) which is continuing to this day. All three stages have undergone upratings and replacements with more powerful engines, and there has been a succession of increasing numbers and sizes of strap-on solid propellant rocket zero stages. Aerojet's original ablative Delta engine had a radiation cooled nozzle exit section, burned N2O4/Aerozine-50 and produced a vacuum thrust of 9000 lbf. This unit also underwent several modifications, ending up with a thrust of 10,200 lbf, and a variety of tank sizes. A throttling (variable thrust) version was developed for a Navy application, and the Delta family could be generally distinguished from Transtage engines by the fact that the Delta gimbal point was at the head end (above the valve assembly), while the Transtage engines (in addition to being smaller) gimballed at the plane of the nozzle throat.

In the early 1970s the expendable launch business was going quite well technically, but changes to reduce cost and increase payload were examined continuously. A series of Delta Alternative Studies was made, some being funded by NASA, but mostly in-house. One such study by Aerojet explored the concept of using a single barrel of the LR-87 engine. This would be used to improve Delta performance, but sufficient development funds were not available and the shuttle was receiving all the emphasis, so the idea died. Another of these studies involved the use of liquid boosters in place of the nine solid boosters then attached to the Thor as a zero stage. The concept was to use either storable or LOX/RP-1 single LR-87 thrust chambers, pressure fed from filament wound tanks. The tanks would use thin metal liners to ensure freedom from leakage - as is still required today for high pressure, light weight filament wound vessels. Aerojet's solid rocket division had done some very encouraging work on high performance solid rocket engine chambers of this same type, and the prices were very attractive. The Aerojet team: Wally Dinsmore, Bob Frew, Lynn Meland. Howard Williams, and Chris Harlambakis from our Los Angeles office had many meetings and technical discussions at Huntington Beach. Two were memorable. The first was in October 1987 when their hosts kept slipping out of the meeting to check their stocks - this was the day the stock market fell drastically. No decisions were made that day. The second meeting almost didn't start. When the Aerojet contingent arrived, there was no one in the building because of an earthquake. The meeting finally got going, and just as Wally was to give his punch line cost and schedule estimate, the building shook with a severe aftershock and plaster dust fell from the ceiling. There were no decisions made that day either. This concept, like the others, couldn't get over the hurdle of the initial development cost - and probably the image of starting up a major new booster program.

Some additional insights into the early part of NASA's long succession of changes are provided by Dan Dembrow, who worked for NASA on the Delta Program at Goddard Space Flight Center:

The Delta launch vehicle was always viewed as an interim launch vehicle in NASA's stable, and was used to retain an intermediate size orbital payload capability until larger launch vehicles were developed. The Delta Project Manager at NASA, Bill Schindler, had a knack for keeping the program alive. He would participate in the launch vehicle assignment process, and when he found that Headquarters was about to kill the Delta on the grounds that a new mission exceeded its capabilities, he would assure them that Delta could do the job. Then he would challenge his technical staff, and often with the aid of the prime contractor, McDonnell Douglas, and our Goddard technical staff, to figure out a way to extend the flight envelope. This process occurred many times, and it was extremely difficult as production launch vehicles are not meant to undergo such constant changes in design. Delta payloads grew from about 200 lbm in low earth orbit in 1960 to about 4100 lbm in geosynchronous orbit by 1990.

In the 1960s, Goddard contracted directly for many of the components (including the second stage from Aerojet), and supplied them to McDonnell Douglas as government furnished equipment (GFE). During this period, Schindler oversold what Delta could do, and each successive payload had us in a quandary. Aerojet was always ready to test changes that would increase the second stage total impulse, and did so frequently. In one such case, a special test was required, and Aerojet went to a lot of trouble to upgrade the test stand for display to NASA management. Among the improvements was a new fail-safe system, and they even went to the point of repainting the bay. At the scheduled date the NASA managers had a schedule conflict, so I was the only NASA observer.

The test took place as scheduled, the instrumentation performed flawlessly, the test values were all nominal, and suddenly the test ended unexpectedly in mid-duration. Nothing within the control room showed anything wrong. When we went out into the test bay, the newly painted walls were on fire. The heat from the fire must have damaged some wiring in the fail-safe system, which promptly terminated the firing.

Aerojet did not realize the critical nature of the test, and this failure almost inadvertently killed the Delta program. Fortunately I was the only NASA observer, and a re-test was successfully conducted within a few days, so Schindler by that time was able to persuade NASA management that all was well. The critical decision was made to fly the mission on Delta.

The customary tug-of-war between the overall vehicle contractor and component system supplier over who should supply how much of the product, began as might be expected. As long as the project remained in Azusa, we had been able to keep the costs below anything Douglas could match. However, at the time when it was to be moved to Sacramento, management required the use of the "new" Commitment Proposal Estimating System which resulted in higher estimated costs. Also, the Douglas Huntington Beach plant was extremely low on work. As a final touch, Aerojet solved the problem by arrogantly sticking to the much higher price to our customer (Douglas). They promptly responded by replacing our system with a similar unit from TRW (surplus LM units) that unfortunately had slightly lower performance. Most of the production for NASA in that time period continued with this TRW engine. Douglas also had kept wearing away Aerojet's share of the project so that we went from supplying the complete stage to the present status of supplying only the thrust chamber assembly and propellant feed lines.

After a painful hiatus, we began work in 1975 on a complete "Fat Delta" stage for the Japanese N-II launch vehicle. At this point we received Air Force funding for performance improvement, one element of which was called the Delta I.T.I.P. (Improved Transtage Injector Program), and used an improved curved face, baffled injector. A still higher performance unit was developed, using a flat faced, baffled injector, and these were used in a two barrel configuration for a classified program. Their excellent performance made this chamber configuration popular, and was the basis for a long but relatively modest rate.

The Delta 3 introduced a new cryogenic upper stage in 1998. However the vehicle began tests just as the satellite market collapsed. It was flown only three times, two of the launches being failures. Meanwhile the most numerous and successful version, the Delta 7000 series, continued in service. The completely new-design Delta 4 was supposed to replace it in service, but the Delta 7000 remained not only lower cost but the most reliable launch vehicle produced in the United States. Nevertheless, in 2008, it was announced that production would be terminated and the Delta 4 would replace it.

The configuration of Delta vehicles was encoded for forty years as follows:

• First digit: basic vehicle configuration:

  This was defined up to 2004 as follows:

  • 0 = Castor 2 solid propellant strap-ons, Long Tank Thor core with MB-3 engine
  • 1 = Castor 2 strap-ons, Extended Long Tank core with MB-3 engine
  • 2 = Castor 2 strap-ons, Extended Long Tank core with RS-27 engine (derived from surplus H-1 engines of the Saturn IB).
  • 3 = Castor 4 solid propellant strap-ons, Extended Long Tank core with RS-27 engine
  • 4 = Castor 4A strap-ons, Extended Long Tank core with MB-3 engine
  • 5 = Castor 4A strap-ons, Extended Long Tank core with RS-27 engine
  • 6 = Castor 4A strap-ons, Extra Extended Long Tank core with RS-27 engine
  • 7 = GEM-40 solid propellant strap-ons, Extra Extended Long Tank core with RS-27A engine
  • 8 = GEM-46 solid propellant strap-ons, Delta-3 strengthened Extra Extended Long Tank core with RS-27A engine
  • 9 = GEM-60 solid propellant strap-ons, Delta-4 Lox/LH2 cryogenic core with RS-68 engine.

  After 2004 this was revised to:

  • 2 = Delta II first stage (previously Delta 6000 and 7000 series)
  • 3 = Delta III first stage (previously Delta 8000 series)
  • 4 = Delta IV first stage (previously Delta 9000 series)

• Second digit: Number of solid propellant strap-ons (0, 3, or 9 prior to Delta IV. 0, 2, or 4 for Delta-4).

• Third digit: Second stage
  • 0 = Delta storable propellant stage with AJ10-118 series engines
  • 1 = Delta storable propellant stage with TR-201 engines (surplus TRW Apollo Lunar Module upper stage engines)
  • 2 = Delta K storable propellant stage with AJ10-118K engine
  • 3 = Delta-3 Lox/LH2 cryogenic upper stage with RL10B-2 engine
  • 4 = Delta-4 Lox/LH2 cryogenic upper stage with 4 m diameter
  • 5 = Delta-4 Lox/LH2 cryogenic upper stage with 5 m diameter

• Fourth digit: Third stage
  • 0 = No third stage
  • 1 = Not used
  • 2 = Not used
  • 3 = Star 37D / TE-364-3 solid propellant kick stage
  • 4 = Star 37E / TE-364-4 solid propellant kick stage
  • 5 = Star-48B / PAM-D solid propellant kick stage (often listed as '0' upper stage with a PAM-D due to the modular nature of the PAM configuration).
  • 6 = Star 37FM solid propellant kick stage
• Optional letter after fourth character: An 'H' here indicated a 'Heavy' configuration. For Delta II, this was use of 46 inch diameter GEM solid strap-on motors in place of the standard Castor motors. For Delta IV, it indicated use of two strap-on Common Booster Cores (CBC) to supplement the CBC on the core stage.
• Dash number: Payload fairing. For Delta II, this indicates the diameter of the fairing in feet. For Delta III or Delta IV, it indicates the length of the fairing in meters.

Manufacturer: Douglas. Launches: 704. Failures: 78. Success Rate: 88.92%. First Launch Date: 1957-01-26. Last Launch Date: 2007-12-20. Launch data is: continuing. Version:

Thor.

Thor IRBM Credit - © Thom

Intermediate range ballistic missile. IOC: 1958. Department of Defence Designation: PGM-17A. Popular Name: Thor. Alternate Designation: SM-75.

Also PTM-17A, USM-75

Historical Essay © Andreas Parsch

Douglas SM-75/PGM-17 Thor

The Thor was the first Intermediate Range Ballistic Missile (IRBM) deployed by the U.S. armed forces. Although its military career was relatively short, its descendants are still in use as space launch vehicles.

Development began in 1954 with USAF studies about a 2400 km (1500 miles) range ballistic missile to complement the long-range ICBM. Soviet ballistic missile progress resulted in a decision in 1955 to develop an IRBM, to be named Thor, as quickly as possible. Using existing components (the Rocketdyne S-3D liquid-fuel rocket motor from the Army's SM-78/PGM-19 Jupiter IRBM, and the inertial guidance unit and Mk.2 reentry vehicle from the SM-65D/CGM-16D Atlas), and requiring the missile to be air-transportable by C-124 Globemaster transport aircraft, the basic design and overall dimensions of the Thor were quickly determined. Go-ahead for development was given in September 1955, and in December 1955, Douglas was selected as prime contractor for the SM-75 Thor IRBM.

Because of the many existing components development was extremely quick, and production of test missiles began as soon as the drawings were completed in August 1956. Testing of the XSM-75 missile began in December 1956, but the first launch attmepts all failed - sometimes in spectacular explosions - and the first successful flight finally occurred in September 1957. Other than the later production missiles, the first XSM-75s had small stabilizing fins at the base of the rocket. After the Soviet Sputnik launch in October 1957, the IRBM program was again accelerated, and Thor was ordered into full production in November 1957. In the next month, the first flight with a fully operational guidance system succeeded. All operational SM-75 missiles were stationed in Great Britain beginning in September 1958. Deployment was completed in June 1960 with 60 missiles at four bases. By then, the Royal Air Force had taken over the operation of the Thor bases and missiles.

The SM-75 was a single-stage rocket, powered by a single Rocketdyne S-3D (designated LR79-NA by the USAF) engine fueled by kerosene and liquid oxygen. The complete main propulsion system was designated as MB-3. Two small Rocketdyne LR101 vernier engines were used for fine-tuning thrust and directional control. The Thor could carry a 1.45 MT W-49 thermonuclear warhead to a distance of 2400 km (1500 miles), and the all-inertial guidance unit achieved an accuracy of 300+ m (1000+ ft) CEP. To protect them from conventional attacks and the weather, the missiles were stored horizontally in soft shelters at the base. After the launch order, the missile would be raised into the vertical, for fueling and launch. This resulted in an overall reaction time of about 10 minutes. Unarmed training missiles were designated USM-75.

During 1962, the Thor was used in a series of exo-atmospheric nuclear tests (called "Starfish", "Bluegill", and "Kingfish"), including the explosion of a 1.4 MT device at an altitude of 450 km (280 miles). Also in 1962, the USAF already started to plan the retirement of the SM-75 IRBM. The intended replacements were the GAM-87/AGM-48 Skybolt ALBM (Air-Launched Ballistic Missile), which was later cancelled, and the Navy's UGM-27 Polaris SLBM (Submarine-Launched Ballistic Missile). The first Thor was removed from base in November 1962, and by September 1963, all Thors had been deactivated and moved back to the USA. Production of Thor IRBMs totaled about 225, with a peak deployment level of 60 missiles.

In June 1963, shortly before its retirement in the UK, all Thor missiles were redesignated in the PGM-17 series as follows:

The final chapter in the military career of the Thor was its use as an anti-satellite weapon. In February 1962 the USAF had started Program 437 to provide for a nuclear ASAT (anti-satellite) capability. Unarmed tests of Thors as ASAT missiles began in February 1964, and by September 1964 the ASAT Thor was declared operational. From that time until the retirement in December 1972, the ADC (Air Defense Command) always had two Thor ASAT launchers on 24h alert. The designation of the Thor in the ASAT role was apparently still PGM-17A, although a redesignation to PIM-17A would have been appropriate.

After retirement as an IRBM, disarmed PGM-17As, as well as new-built Thors, were used by the USAF as space launch vehicles under the basic designation of SLV-2. The Thor was developed by McDonnell-Douglas (now Boeing) into the very successful Delta family of space launchers, still in use today. In 1990 the official designation of SB-3A was assigned to the USAF's Delta II rockets.

Note: Data given by several sources show slight variations. Figures given below may therefore be inaccurate!

Data for PGM-17A:

[1] James N. Gibson: "Nuclear Weapons of the United States", Schiffer Publishing Ltd, 1996
[2] Bill Gunston: "The Illustrated Encyclopedia of Rockets and Missiles", Salamander Books Ltd, 1979

Liftoff Thrust: 666.000 kN (149,722 lbf). Total Mass: 50,000 kg (110,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 19.82 m (65.02 ft). Span: 2.74 m (8.98 ft). Standard warhead mass: 1,000 kg (2,200 lb). Maximum range: 2,400 km (1,400 mi). Number Standard Warheads: 1. Standard RV: Mk. 2. Standard warhead: W49. Standard warhead yield: 1,440 KT. Standard warhead CEP: 0.97 km (0.60 mi). Boost Propulsion: Liquid rocket, Lox/Kerosene. Guidance: Inertial. Maximum speed: 17,740 kph (11,020 mph). Development Cost $: 500.000 million. in: 1958 average dollars. Recurring Price $: 6.250 million. Total Number Built: 224. Total Development Built: 64. Total Production Built: 160. Flyaway Unit Cost $: 0.750 million. in: 1958 unit dollars. Version:

Thor DM-18.

RAF Training Launch Credit - Larry Rhoads

Status: Retired 1958.

Single stage vehicle adapted from Thor IRBM with no upper stage.

Sixty Thors were deployed to missile sites in Great Britain under Project Emily. Philip Payne worked for Rocketdyne as their manager in England. He recalls:

Those days I worked for Rocketdyne as the manager in England of Project Emily. Our mission: get 60 Thors aimed at Khrushchev’s privates. Things were going badly for lots of reasons, many of them lack of earnest concentration by many Americans in corporations as well as USAF. I was p....d and often loudly said so.

One day a dignified, little American man came to me at Feltwell, Cambridgeshire, England, site of the first squadron (if we could ever get it installed and checked out) and told me he heard I was the one to talk to find out what was wrong. I was bad on names then, in my youth and so for hours as I laid it on him, I did not realize until late in the day I was talking to the American Secretary of Defense, Charlie Wilson.

I was so unpolitical an engineer turned executive, that I did not bother to tell my company of this until, receiving a muted blast vis á vis Douglas, they told me. Douglas sent over Bill Duval to replace Earl Neff.....

Thereafter things improved. After a few years the Thors were withdrawn from Britain (and the Jupiters from Turkey) as part of the secret codicil of Kennedy’s deal to end the Cuban Missile Crisis.

Launches: 18. Failures: 9. First Launch Date: 1957-01-26. Last Launch Date: 1958-08-06. Apogee: 520 km (320 mi). Associated Spacecraft: DMSP Block 4A. Liftoff Thrust: 667.200 kN (149,993 lbf). Total Mass: 49,340 kg (108,770 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 22.00 m (72.00 ft). Development Cost $: 500.000 million. in: 1958 average dollars. Launch Price $: 4.930 million. in: 1985 price dollars. Total Development Built: 64. Total Production Built: 160. Flyaway Unit Cost $: 0.750 million. in: 1958 unit dollars.

• Stage1: 1 x Thor DM-19. Gross Mass: 49,340 kg (108,770 lb). Empty Mass: 3,125 kg (6,889 lb). Motor: 1 x LR79-7. Thrust (vac): 758.711 kN (170,565 lbf). Isp: 282 sec. Burn time: 165 sec. Length: 18.42 m (60.43 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage1: 1 x Thor DM-19. Gross Mass: 49,340 kg (108,770 lb). Empty Mass: 3,125 kg (6,889 lb). Motor: 1 x LR79-7. Thrust (vac): 758.711 kN (170,565 lbf). Isp: 282 sec. Burn time: 165 sec. Length: 18.42 m (60.43 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage1: 1 x Thor DM-19. Gross Mass: 49,340 kg (108,770 lb). Empty Mass: 3,125 kg (6,889 lb). Motor: 1 x LR79-7. Thrust (vac): 758.711 kN (170,565 lbf). Isp: 282 sec. Burn time: 165 sec. Length: 18.42 m (60.43 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage1: 1 x Thor DM-19. Gross Mass: 49,340 kg (108,770 lb). Empty Mass: 3,125 kg (6,889 lb). Motor: 1 x LR79-7. Thrust (vac): 758.711 kN (170,565 lbf). Isp: 282 sec. Burn time: 165 sec. Length: 18.42 m (60.43 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Scout X-3M-4. Gross Mass: 300 kg (660 lb). Motor: 1 x MG-18. Length: 1.50 m (4.90 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.

LEO Payload: 770 kg (1,690 lb). Associated Spacecraft: Aurora, Calsphere, DMSP Block 4A, DMSP Block 5A, DMSP Block 5B, DMSP Block 5C, SECOR, SESP. Liftoff Thrust: 667.200 kN (149,993 lbf). Total Mass: 51,810 kg (114,220 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 24.00 m (78.00 ft). Flyaway Unit Cost $: 11.890 million. in: 1985 unit dollars. Version:

Thor Burner 1.

Thor Burner Launch 2 Credit - Larry Rhoads

Status: Retired 1966.

Two stage vehicle consisting of 1 x Thor DM-18A + 1 x FW4S

Launches: 4. Failures: 1. First Launch Date: 1965-05-20. Last Launch Date: 1966-03-31. Apogee: 1,000 km (600 mi). Liftoff Thrust: 668.000 kN (150,172 lbf). Total Mass: 50,000 kg (110,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 23.00 m (75.00 ft).

• Stage1: 1 x Thor DM-19. Gross Mass: 49,340 kg (108,770 lb). Empty Mass: 3,125 kg (6,889 lb). Motor: 1 x LR79-7. Thrust (vac): 758.711 kN (170,565 lbf). Isp: 282 sec. Burn time: 165 sec. Length: 18.42 m (60.43 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Altair 3. Gross Mass: 301 kg (663 lb). Empty Mass: 25 kg (55 lb). Motor: 1 x FW-4S TEM640. Thrust (vac): 27.400 kN (6,160 lbf). Isp: 280 sec. Burn time: 27 sec. Length: 2.53 m (8.30 ft). Diameter: 0.64 m (2.09 ft). Propellants: Solid.

• Stage1: 1 x Thor DM-19. Gross Mass: 49,340 kg (108,770 lb). Empty Mass: 3,125 kg (6,889 lb). Motor: 1 x LR79-7. Thrust (vac): 758.711 kN (170,565 lbf). Isp: 282 sec. Burn time: 165 sec. Length: 18.42 m (60.43 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Burner 2. Gross Mass: 774 kg (1,706 lb). Empty Mass: 116 kg (255 lb). Motor: 1 x Star 37. Thrust (vac): 43.551 kN (9,791 lbf). Isp: 285 sec. Burn time: 42 sec. Length: 0.84 m (2.75 ft). Diameter: 0.66 m (2.16 ft). Propellants: Solid.

• Stage3: 1 x Burner 2. Gross Mass: 774 kg (1,706 lb). Empty Mass: 116 kg (255 lb). Motor: 1 x Star 37. Thrust (vac): 43.551 kN (9,791 lbf). Isp: 285 sec. Burn time: 42 sec. Length: 0.84 m (2.75 ft). Diameter: 0.66 m (2.16 ft). Propellants: Solid.

• Stage1: 1 x Thor DM-19. Gross Mass: 49,340 kg (108,770 lb). Empty Mass: 3,125 kg (6,889 lb). Motor: 1 x LR79-7. Thrust (vac): 758.711 kN (170,565 lbf). Isp: 282 sec. Burn time: 165 sec. Length: 18.42 m (60.43 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Star 37B. Gross Mass: 718 kg (1,582 lb). Empty Mass: 64 kg (141 lb). Motor: 1 x Star 37B. Thrust (vac): 45.000 kN (10,116 lbf). Length: 1.50 m (4.90 ft). Diameter: 0.94 m (3.08 ft). Propellants: Solid.

• Stage3: 1 x Star 26B. Gross Mass: 261 kg (575 lb). Empty Mass: 23 kg (50 lb). Motor: 1 x Star 26B. Thrust (vac): 34.627 kN (7,784 lbf). Burn time: 18 sec. Length: 0.80 m (2.62 ft). Diameter: 0.66 m (2.16 ft). Propellants: Solid.

Launches: 2. First Launch Date: 1962-01-15. Last Launch Date: 1962-07-18. Apogee: 1,500 km (900 mi). Associated Spacecraft: Program 437, Program 922. Liftoff Thrust: 743.000 kN (167,033 lbf). Total Mass: 50,000 kg (110,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 21.70 m (71.10 ft).

• Stage1: 1 x Thor DM-21. Gross Mass: 48,354 kg (106,602 lb). Empty Mass: 2,948 kg (6,499 lb). Motor: 1 x MB-3-1. Thrust (vac): 760.643 kN (170,999 lbf). Isp: 285 sec. Burn time: 164 sec. Length: 18.41 m (60.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage1: 1 x Thor DM-19. Gross Mass: 49,340 kg (108,770 lb). Empty Mass: 3,125 kg (6,889 lb). Motor: 1 x LR79-7. Thrust (vac): 758.711 kN (170,565 lbf). Isp: 282 sec. Burn time: 165 sec. Length: 18.42 m (60.43 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage1: 1 x Thor DM-19. Gross Mass: 49,340 kg (108,770 lb). Empty Mass: 3,125 kg (6,889 lb). Motor: 1 x LR79-7. Thrust (vac): 758.711 kN (170,565 lbf). Isp: 282 sec. Burn time: 165 sec. Length: 18.42 m (60.43 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

Launches: 3. Failures: 1. First Launch Date: 1964-03-24. Last Launch Date: 1965-02-23. Apogee: 75 km (46 mi). Associated Spacecraft: Asset. Liftoff Thrust: 668.000 kN (150,172 lbf). Total Mass: 55,000 kg (121,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 26.90 m (88.20 ft).

• Stage1: 1 x Thor DM-19. Gross Mass: 49,340 kg (108,770 lb). Empty Mass: 3,125 kg (6,889 lb). Motor: 1 x LR79-7. Thrust (vac): 758.711 kN (170,565 lbf). Isp: 282 sec. Burn time: 165 sec. Length: 18.42 m (60.43 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta A. Gross Mass: 2,164 kg (4,770 lb). Empty Mass: 694 kg (1,530 lb). Motor: 1 x AJ10-118. Thrust (vac): 33.803 kN (7,599 lbf). Isp: 271 sec. Burn time: 115 sec. Length: 5.36 m (17.58 ft). Diameter: 0.84 m (2.75 ft). Propellants: Nitric acid/UDMH.

• Stage1: 1 x Thor DM-19. Gross Mass: 49,340 kg (108,770 lb). Empty Mass: 3,125 kg (6,889 lb). Motor: 1 x LR79-7. Thrust (vac): 758.711 kN (170,565 lbf). Isp: 282 sec. Burn time: 165 sec. Length: 18.42 m (60.43 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

Launches: 5. Failures: 1. First Launch Date: 1976-09-11. Last Launch Date: 1980-07-15. LEO Payload: 500 kg (1,100 lb). to: 300 km Orbit. at: 28.00 degrees. Apogee: 1,000 km (600 mi). Associated Spacecraft: DMSP Block 5D. Liftoff Thrust: 750.000 kN (168,600 lbf). Total Mass: 49,500 kg (109,100 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 23.00 m (75.00 ft).

• Stage1: 1 x Thor DM-19. Gross Mass: 49,340 kg (108,770 lb). Empty Mass: 3,125 kg (6,889 lb). Motor: 1 x LR79-7. Thrust (vac): 758.711 kN (170,565 lbf). Isp: 282 sec. Burn time: 165 sec. Length: 18.42 m (60.43 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Star 37XE. Gross Mass: 900 kg (1,980 lb). Empty Mass: 67 kg (147 lb). Motor: 1 x Star 37XE. Thrust (vac): 45.000 kN (10,116 lbf). Burn time: 66 sec. Length: 1.70 m (5.50 ft). Diameter: 0.94 m (3.08 ft). Propellants: Solid.

Launches: 3. Failures: 1. First Launch Date: 1958-04-24. Last Launch Date: 1958-07-23. LEO Payload: 120 kg (260 lb). to: 640 km Orbit. at: 48.00 degrees. Apogee: 1,600 km (900 mi). Associated Spacecraft: Pioneer 0-1-2, Pioneer 5, S-2, Tiros, Transit. Liftoff Thrust: 667.200 kN (149,993 lbf). Total Mass: 51,608 kg (113,776 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 30.00 m (98.00 ft). Flyaway Unit Cost $: 8.930 million. in: 1985 unit dollars.

• Stage1: 1 x Thor DM-19. Gross Mass: 49,340 kg (108,770 lb). Empty Mass: 3,125 kg (6,889 lb). Motor: 1 x LR79-7. Thrust (vac): 758.711 kN (170,565 lbf). Isp: 282 sec. Burn time: 165 sec. Length: 18.42 m (60.43 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Able. Gross Mass: 1,884 kg (4,153 lb). Empty Mass: 429 kg (945 lb). Motor: 1 x AJ10-40. Thrust (vac): 34.690 kN (7,799 lbf). Isp: 270 sec. Burn time: 115 sec. Length: 5.67 m (18.60 ft). Diameter: 0.81 m (2.65 ft). Propellants: Nitric acid/UDMH.

• Stage1: 1 x Thor DM-19. Gross Mass: 49,340 kg (108,770 lb). Empty Mass: 3,125 kg (6,889 lb). Motor: 1 x LR79-7. Thrust (vac): 758.711 kN (170,565 lbf). Isp: 282 sec. Burn time: 165 sec. Length: 18.42 m (60.43 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Able. Gross Mass: 1,884 kg (4,153 lb). Empty Mass: 429 kg (945 lb). Motor: 1 x AJ10-40. Thrust (vac): 34.690 kN (7,799 lbf). Isp: 270 sec. Burn time: 115 sec. Length: 5.67 m (18.60 ft). Diameter: 0.81 m (2.65 ft). Propellants: Nitric acid/UDMH.

• Stage1: 1 x Thor DM-19. Gross Mass: 49,340 kg (108,770 lb). Empty Mass: 3,125 kg (6,889 lb). Motor: 1 x LR79-7. Thrust (vac): 758.711 kN (170,565 lbf). Isp: 282 sec. Burn time: 165 sec. Length: 18.42 m (60.43 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Able. Gross Mass: 1,884 kg (4,153 lb). Empty Mass: 429 kg (945 lb). Motor: 1 x AJ10-40. Thrust (vac): 34.690 kN (7,799 lbf). Isp: 270 sec. Burn time: 115 sec. Length: 5.67 m (18.60 ft). Diameter: 0.81 m (2.65 ft). Propellants: Nitric acid/UDMH.

• Stage1: 1 x Thor DM-19. Gross Mass: 49,340 kg (108,770 lb). Empty Mass: 3,125 kg (6,889 lb). Motor: 1 x LR79-7. Thrust (vac): 758.711 kN (170,565 lbf). Isp: 282 sec. Burn time: 165 sec. Length: 18.42 m (60.43 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Able. Gross Mass: 1,884 kg (4,153 lb). Empty Mass: 429 kg (945 lb). Motor: 1 x AJ10-40. Thrust (vac): 34.690 kN (7,799 lbf). Isp: 270 sec. Burn time: 115 sec. Length: 5.67 m (18.60 ft). Diameter: 0.81 m (2.65 ft). Propellants: Nitric acid/UDMH.

• Stage3: 1 x Altair 1. Gross Mass: 238 kg (524 lb). Empty Mass: 30 kg (66 lb). Motor: 1 x X-248. Thrust (vac): 12.450 kN (2,799 lbf). Isp: 256 sec. Burn time: 38 sec. Length: 1.83 m (6.00 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.

• Stage1: 1 x Thor DM-19. Gross Mass: 49,340 kg (108,770 lb). Empty Mass: 3,125 kg (6,889 lb). Motor: 1 x LR79-7. Thrust (vac): 758.711 kN (170,565 lbf). Isp: 282 sec. Burn time: 165 sec. Length: 18.42 m (60.43 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Able. Gross Mass: 1,884 kg (4,153 lb). Empty Mass: 429 kg (945 lb). Motor: 1 x AJ10-40. Thrust (vac): 34.690 kN (7,799 lbf). Isp: 270 sec. Burn time: 115 sec. Length: 5.67 m (18.60 ft). Diameter: 0.81 m (2.65 ft). Propellants: Nitric acid/UDMH.

• Stage3: 1 x Altair 1. Gross Mass: 238 kg (524 lb). Empty Mass: 30 kg (66 lb). Motor: 1 x X-248. Thrust (vac): 12.450 kN (2,799 lbf). Isp: 256 sec. Burn time: 38 sec. Length: 1.83 m (6.00 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.

• Stage1: 1 x Thor DM-19. Gross Mass: 49,340 kg (108,770 lb). Empty Mass: 3,125 kg (6,889 lb). Motor: 1 x LR79-7. Thrust (vac): 758.711 kN (170,565 lbf). Isp: 282 sec. Burn time: 165 sec. Length: 18.42 m (60.43 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Able. Gross Mass: 1,884 kg (4,153 lb). Empty Mass: 429 kg (945 lb). Motor: 1 x AJ10-40. Thrust (vac): 34.690 kN (7,799 lbf). Isp: 270 sec. Burn time: 115 sec. Length: 5.67 m (18.60 ft). Diameter: 0.81 m (2.65 ft). Propellants: Nitric acid/UDMH.

• Stage3: 1 x Altair 1. Gross Mass: 238 kg (524 lb). Empty Mass: 30 kg (66 lb). Motor: 1 x X-248. Thrust (vac): 12.450 kN (2,799 lbf). Isp: 256 sec. Burn time: 38 sec. Length: 1.83 m (6.00 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.

LEO Payload: 150 kg (330 lb). to: 1,100 km Orbit. at: 90.00 degrees. Apogee: 1,500 km (900 mi). Associated Spacecraft: Anna, APL, Calsphere, Courier, DODECAPOLE, GRAB, Injun, Lofti, Lofti 2, SECOR, Surcal, Tempsat, TRAAC, Transit. Liftoff Thrust: 667.200 kN (149,993 lbf). Total Mass: 53,000 kg (116,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 29.00 m (95.00 ft). Flyaway Unit Cost $: 12.830 million. in: 1985 unit dollars.

• Stage1: 1 x Thor DM-21. Gross Mass: 48,354 kg (106,602 lb). Empty Mass: 2,948 kg (6,499 lb). Motor: 1 x MB-3-1. Thrust (vac): 760.643 kN (170,999 lbf). Isp: 285 sec. Burn time: 164 sec. Length: 18.41 m (60.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Able-Star. Gross Mass: 4,497 kg (9,914 lb). Empty Mass: 599 kg (1,320 lb). Motor: 1 x AJ10-104. Thrust (vac): 36.024 kN (8,099 lbf). Isp: 280 sec. Burn time: 296 sec. Length: 4.52 m (14.82 ft). Diameter: 1.40 m (4.50 ft). Propellants: Nitric acid/UDMH.

• Stage1: 1 x Thor DM-21. Gross Mass: 48,354 kg (106,602 lb). Empty Mass: 2,948 kg (6,499 lb). Motor: 1 x MB-3-1. Thrust (vac): 760.643 kN (170,999 lbf). Isp: 285 sec. Burn time: 164 sec. Length: 18.41 m (60.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Able-Star. Gross Mass: 4,497 kg (9,914 lb). Empty Mass: 599 kg (1,320 lb). Motor: 1 x AJ10-104. Thrust (vac): 36.024 kN (8,099 lbf). Isp: 280 sec. Burn time: 296 sec. Length: 4.52 m (14.82 ft). Diameter: 1.40 m (4.50 ft). Propellants: Nitric acid/UDMH.

LEO Payload: 1,400 kg (3,000 lb). to: 185 km Orbit. at: 28.00 degrees. Liftoff Thrust: 667.200 kN (149,993 lbf). Total Mass: 53,000 kg (116,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 30.00 m (98.00 ft). Version:

Thor Agena A.

Thor-Agena A Credit - US Air Force

Status: Retired 1960. Department of Defence Designation: SLV-2. Manufacturer's Designation: DSV-2A.

Two stage vehicle consisting of 1 x Thor DM-18A + 1 x Agena A

Launches: 16. Failures: 6. First Launch Date: 1959-01-21. Last Launch Date: 1960-09-13. LEO Payload: 250 kg (550 lb). Apogee: 1,000 km (600 mi). Associated Spacecraft: KH-1. Liftoff Thrust: 667.200 kN (149,993 lbf). Total Mass: 53,130 kg (117,130 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 28.00 m (91.00 ft). Flyaway Unit Cost $: 10.730 million. in: 1985 unit dollars.

• Stage1: 1 x Thor DM-19. Gross Mass: 49,340 kg (108,770 lb). Empty Mass: 3,125 kg (6,889 lb). Motor: 1 x LR79-7. Thrust (vac): 758.711 kN (170,565 lbf). Isp: 282 sec. Burn time: 165 sec. Length: 18.42 m (60.43 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Agena A. Gross Mass: 3,790 kg (8,350 lb). Empty Mass: 885 kg (1,951 lb). Motor: 1 x Bell 8048. Thrust (vac): 68.950 kN (15,501 lbf). Isp: 276 sec. Burn time: 120 sec. Length: 4.73 m (15.51 ft). Diameter: 1.52 m (4.98 ft). Propellants: Nitric acid/UDMH.

Launches: 40. Failures: 8. Success Rate: 80.00%. First Launch Date: 1960-10-26. Last Launch Date: 1963-01-16. Apogee: 1,000 km (600 mi). Associated Spacecraft: Alouette, ERS, Ferret, KH-2, KH-3, KH-4, KH-5, Midas, Oscar. Liftoff Thrust: 667.200 kN (149,993 lbf). Total Mass: 56,507 kg (124,576 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 31.00 m (101.00 ft). Flyaway Unit Cost $: 13.630 million. in: 1985 unit dollars.

• Stage1: 1 x Thor DM-21. Gross Mass: 48,354 kg (106,602 lb). Empty Mass: 2,948 kg (6,499 lb). Motor: 1 x MB-3-1. Thrust (vac): 760.643 kN (170,999 lbf). Isp: 285 sec. Burn time: 164 sec. Length: 18.41 m (60.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Agena B. Gross Mass: 7,167 kg (15,800 lb). Empty Mass: 867 kg (1,911 lb). Motor: 1 x Bell 8081. Thrust (vac): 71.166 kN (15,999 lbf). Isp: 285 sec. Burn time: 240 sec. Length: 7.09 m (23.26 ft). Diameter: 1.52 m (4.98 ft). Propellants: Nitric acid/UDMH.

Launches: 3. Failures: 1. First Launch Date: 1964-01-25. Last Launch Date: 1965-11-29. Apogee: 1,000 km (600 mi). Associated Spacecraft: Echo 2, Nimbus. Liftoff Thrust: 756.000 kN (169,955 lbf). Total Mass: 56,500 kg (124,500 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 27.20 m (89.20 ft).

• Stage1: 1 x Thor DM-19. Gross Mass: 49,340 kg (108,770 lb). Empty Mass: 3,125 kg (6,889 lb). Motor: 1 x LR79-7. Thrust (vac): 758.711 kN (170,565 lbf). Isp: 282 sec. Burn time: 165 sec. Length: 18.42 m (60.43 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Agena B. Gross Mass: 7,167 kg (15,800 lb). Empty Mass: 867 kg (1,911 lb). Motor: 1 x Bell 8081. Thrust (vac): 71.166 kN (15,999 lbf). Isp: 285 sec. Burn time: 240 sec. Length: 7.09 m (23.26 ft). Diameter: 1.52 m (4.98 ft). Propellants: Nitric acid/UDMH.

Launches: 2. First Launch Date: 1963-06-29. Last Launch Date: 1966-05-15. LEO Payload: 400 kg (880 lb). to: 1,000 km Orbit. at: 100.00 degrees. Apogee: 2,000 km (1,200 mi). Associated Spacecraft: Alouette, DME, Ferret, Nimbus. Liftoff Thrust: 1,571.000 kN (353,174 lbf). Total Mass: 67,500 kg (148,800 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 31.00 m (101.00 ft). Flyaway Unit Cost $: 19.560 million. in: 1985 unit dollars.

• Stage0: 3 x Castor 1. Gross Mass: 3,852 kg (8,492 lb). Empty Mass: 535 kg (1,179 lb). Motor: 1 x M33-20-4. Thrust (vac): 286.001 kN (64,296 lbf). Isp: 247 sec. Burn time: 27 sec. Length: 5.92 m (19.42 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor TA. Gross Mass: 49,442 kg (109,000 lb). Empty Mass: 3,175 kg (6,999 lb). Motor: 1 x MB-3-3. Thrust (vac): 866.710 kN (194,844 lbf). Isp: 290 sec. Burn time: 150 sec. Length: 18.41 m (60.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Agena B. Gross Mass: 7,167 kg (15,800 lb). Empty Mass: 867 kg (1,911 lb). Motor: 1 x Bell 8081. Thrust (vac): 71.166 kN (15,999 lbf). Isp: 285 sec. Burn time: 240 sec. Length: 7.09 m (23.26 ft). Diameter: 1.52 m (4.98 ft). Propellants: Nitric acid/UDMH.

Launches: 13. Failures: 1. First Launch Date: 1962-06-28. Last Launch Date: 1963-07-19. Associated Spacecraft: AFP-43, Calsphere, DODECAPOLE, Ferret, GGSE, GRAB, Injun, KH-4, KH-5, Lofti, NRL ELINT, Oscar, RADOSE, SECOR, Starfish, SURCAL, Timation. Liftoff Thrust: 667.200 kN (149,993 lbf). Total Mass: 56,507 kg (124,576 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 31.00 m (101.00 ft). Flyaway Unit Cost $: 13.630 million. in: 1985 unit dollars.

• Stage1: 1 x Thor DM-21. Gross Mass: 48,354 kg (106,602 lb). Empty Mass: 2,948 kg (6,499 lb). Motor: 1 x MB-3-1. Thrust (vac): 760.643 kN (170,999 lbf). Isp: 285 sec. Burn time: 164 sec. Length: 18.41 m (60.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Agena D. Gross Mass: 6,821 kg (15,037 lb). Empty Mass: 673 kg (1,483 lb). Motor: 1 x Bell 8096. Thrust (vac): 71.166 kN (15,999 lbf). Isp: 300 sec. Burn time: 265 sec. Length: 7.09 m (23.26 ft). Diameter: 1.52 m (4.98 ft). Propellants: Nitric acid/UDMH.

• Stage1: 1 x Thor DM-19. Gross Mass: 49,340 kg (108,770 lb). Empty Mass: 3,125 kg (6,889 lb). Motor: 1 x LR79-7. Thrust (vac): 758.711 kN (170,565 lbf). Isp: 282 sec. Burn time: 165 sec. Length: 18.42 m (60.43 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Agena D. Gross Mass: 6,821 kg (15,037 lb). Empty Mass: 673 kg (1,483 lb). Motor: 1 x Bell 8096. Thrust (vac): 71.166 kN (15,999 lbf). Isp: 300 sec. Burn time: 265 sec. Length: 7.09 m (23.26 ft). Diameter: 1.52 m (4.98 ft). Propellants: Nitric acid/UDMH.

Launches: 60. Failures: 4. Success Rate: 93.33%. First Launch Date: 1963-02-28. Last Launch Date: 1968-01-17. Apogee: 1,000 km (600 mi). Associated Spacecraft: Ferret, KH-4, KH-4A, KH-5, KH-6, OGO, P 11, Pageos, SSF, Starflash. Liftoff Thrust: 1,571.000 kN (353,174 lbf). Total Mass: 67,819 kg (149,515 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 31.00 m (101.00 ft). Flyaway Unit Cost $: 19.560 million. in: 1985 unit dollars.

• Stage0: 3 x Castor 1. Gross Mass: 3,852 kg (8,492 lb). Empty Mass: 535 kg (1,179 lb). Motor: 1 x M33-20-4. Thrust (vac): 286.001 kN (64,296 lbf). Isp: 247 sec. Burn time: 27 sec. Length: 5.92 m (19.42 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor TA. Gross Mass: 49,442 kg (109,000 lb). Empty Mass: 3,175 kg (6,999 lb). Motor: 1 x MB-3-3. Thrust (vac): 866.710 kN (194,844 lbf). Isp: 290 sec. Burn time: 150 sec. Length: 18.41 m (60.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Agena D. Gross Mass: 6,821 kg (15,037 lb). Empty Mass: 673 kg (1,483 lb). Motor: 1 x Bell 8096. Thrust (vac): 71.166 kN (15,999 lbf). Isp: 300 sec. Burn time: 265 sec. Length: 7.09 m (23.26 ft). Diameter: 1.52 m (4.98 ft). Propellants: Nitric acid/UDMH.

Launches: 30. Failures: 2. Success Rate: 93.33%. First Launch Date: 1966-08-09. Last Launch Date: 1971-12-14. Apogee: 1,000 km (600 mi). Associated Spacecraft: ASTEX, Ferret, KH-4A, KH-4B, Nimbus, NOSS, NRL ELINT, SECOR, SERT, SOICAL, SSF, Surcal, Tempsat, Timation, TOPO. Liftoff Thrust: 1,444.000 kN (324,624 lbf). Total Mass: 91,400 kg (201,500 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 32.90 m (107.90 ft).

• Stage0: 3 x Castor 1. Gross Mass: 3,852 kg (8,492 lb). Empty Mass: 535 kg (1,179 lb). Motor: 1 x M33-20-4. Thrust (vac): 286.001 kN (64,296 lbf). Isp: 247 sec. Burn time: 27 sec. Length: 5.92 m (19.42 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor LT. Gross Mass: 70,354 kg (155,104 lb). Empty Mass: 3,715 kg (8,190 lb). Motor: 1 x MB-3-3. Thrust (vac): 866.710 kN (194,844 lbf). Isp: 290 sec. Burn time: 215 sec. Length: 21.43 m (70.30 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Agena D. Gross Mass: 6,821 kg (15,037 lb). Empty Mass: 673 kg (1,483 lb). Motor: 1 x Bell 8096. Thrust (vac): 71.166 kN (15,999 lbf). Isp: 300 sec. Burn time: 265 sec. Length: 7.09 m (23.26 ft). Diameter: 1.52 m (4.98 ft). Propellants: Nitric acid/UDMH.

Launches: 13. Failures: 1. First Launch Date: 1969-06-05. Last Launch Date: 1972-05-25. Apogee: 1,000 km (600 mi). Associated Spacecraft: Ferret, KH-4B, OGO, SSF. Liftoff Thrust: 1,571.000 kN (353,174 lbf). Total Mass: 88,731 kg (195,618 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 34.00 m (111.00 ft). Flyaway Unit Cost $: 22.170 million. in: 1985 unit dollars.

• Stage0: 3 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor LT. Gross Mass: 70,354 kg (155,104 lb). Empty Mass: 3,715 kg (8,190 lb). Motor: 1 x MB-3-3. Thrust (vac): 866.710 kN (194,844 lbf). Isp: 290 sec. Burn time: 215 sec. Length: 21.43 m (70.30 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Agena D. Gross Mass: 6,821 kg (15,037 lb). Empty Mass: 673 kg (1,483 lb). Motor: 1 x Bell 8096. Thrust (vac): 71.166 kN (15,999 lbf). Isp: 300 sec. Burn time: 265 sec. Length: 7.09 m (23.26 ft). Diameter: 1.52 m (4.98 ft). Propellants: Nitric acid/UDMH.

Launches: 12. Failures: 1. First Launch Date: 1960-05-13. Last Launch Date: 1962-09-18. LEO Payload: 226 kg (498 lb). Payload: 45 kg (99 lb). to a: Geosynchronous transfer trajectory. Apogee: 100,000 km (60,000 mi). Associated Spacecraft: Ariel, Echo, EPE, OSO, P-14, Telstar, Tiros. Liftoff Thrust: 667.200 kN (149,993 lbf). Total Mass: 54,050 kg (119,150 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 31.00 m (101.00 ft). Flyaway Unit Cost $: 7.270 million. in: 1985 unit dollars.

• Stage1: 1 x Thor DM-19. Gross Mass: 49,340 kg (108,770 lb). Empty Mass: 3,125 kg (6,889 lb). Motor: 1 x LR79-7. Thrust (vac): 758.711 kN (170,565 lbf). Isp: 282 sec. Burn time: 165 sec. Length: 18.42 m (60.43 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta 104. Gross Mass: 4,472 kg (9,859 lb). Empty Mass: 590 kg (1,300 lb). Motor: 1 x AJ10-104. Thrust (vac): 35.098 kN (7,890 lbf). Isp: 278 sec. Burn time: 296 sec. Length: 5.88 m (19.29 ft). Diameter: 1.40 m (4.50 ft). Propellants: Nitric acid/UDMH.

• Stage3: 1 x Altair 1. Gross Mass: 238 kg (524 lb). Empty Mass: 30 kg (66 lb). Motor: 1 x X-248. Thrust (vac): 12.450 kN (2,799 lbf). Isp: 256 sec. Burn time: 38 sec. Length: 1.83 m (6.00 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.

Launches: 2. First Launch Date: 1962-10-02. Last Launch Date: 1962-10-27. LEO Payload: 250 kg (550 lb). Payload: 68 kg (149 lb). to a: Geosynchronous transfer trajectory. Apogee: 100,000 km (60,000 mi). Associated Spacecraft: EPE. Liftoff Thrust: 667.200 kN (149,993 lbf). Total Mass: 50,756 kg (111,897 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 31.00 m (101.00 ft). Flyaway Unit Cost $: 9.590 million. in: 1985 unit dollars.

• Stage1: 1 x Thor DM-21. Gross Mass: 48,354 kg (106,602 lb). Empty Mass: 2,948 kg (6,499 lb). Motor: 1 x MB-3-1. Thrust (vac): 760.643 kN (170,999 lbf). Isp: 285 sec. Burn time: 164 sec. Length: 18.41 m (60.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta A. Gross Mass: 2,164 kg (4,770 lb). Empty Mass: 694 kg (1,530 lb). Motor: 1 x AJ10-118. Thrust (vac): 33.803 kN (7,599 lbf). Isp: 271 sec. Burn time: 115 sec. Length: 5.36 m (17.58 ft). Diameter: 0.84 m (2.75 ft). Propellants: Nitric acid/UDMH.

• Stage3: 1 x Altair 1. Gross Mass: 238 kg (524 lb). Empty Mass: 30 kg (66 lb). Motor: 1 x X-248. Thrust (vac): 12.450 kN (2,799 lbf). Isp: 256 sec. Burn time: 38 sec. Length: 1.83 m (6.00 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.

Launches: 9. Failures: 1. First Launch Date: 1962-12-13. Last Launch Date: 1964-03-19. LEO Payload: 370 kg (810 lb). Payload: 68 kg (149 lb). to a: Geosynchronous transfer trajectory. Apogee: 40,000 km (24,000 mi). Associated Spacecraft: AE, BE, Relay, Syncom, Telstar, Tiros. Liftoff Thrust: 667.200 kN (149,993 lbf). Total Mass: 51,285 kg (113,064 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 31.00 m (101.00 ft). Flyaway Unit Cost $: 9.590 million. in: 1985 unit dollars.

• Stage1: 1 x Thor DM-21. Gross Mass: 48,354 kg (106,602 lb). Empty Mass: 2,948 kg (6,499 lb). Motor: 1 x MB-3-1. Thrust (vac): 760.643 kN (170,999 lbf). Isp: 285 sec. Burn time: 164 sec. Length: 18.41 m (60.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta D. Gross Mass: 2,693 kg (5,937 lb). Empty Mass: 545 kg (1,201 lb). Motor: 1 x AJ10-118D. Thrust (vac): 33.695 kN (7,575 lbf). Isp: 278 sec. Burn time: 170 sec. Length: 5.58 m (18.30 ft). Diameter: 0.84 m (2.75 ft). Propellants: Nitric acid/UDMH.

• Stage3: 1 x Altair 1. Gross Mass: 238 kg (524 lb). Empty Mass: 30 kg (66 lb). Motor: 1 x X-248. Thrust (vac): 12.450 kN (2,799 lbf). Isp: 256 sec. Burn time: 38 sec. Length: 1.83 m (6.00 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.

Payload: 82 kg (180 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: AE, EPE, IMP, OSO, Tiros. Liftoff Thrust: 667.200 kN (149,993 lbf). Total Mass: 51,285 kg (113,064 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 31.00 m (101.00 ft). Flyaway Unit Cost $: 9.590 million. in: 1985 unit dollars. Version:

Thor Delta C. Status: Retired 1967.

Three stage vehicle consisting of 1 x Thor DSV-2A + 1 x Delta D + 1 x Altair 2

Launches: 10. Failures: 1. First Launch Date: 1963-11-27. Last Launch Date: 1967-03-08. LEO Payload: 81 kg (178 lb). Apogee: 100,000 km (60,000 mi). Liftoff Thrust: 756.000 kN (169,955 lbf). Total Mass: 52,000 kg (114,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 27.50 m (90.20 ft).

• Stage1: 1 x Thor DM-21. Gross Mass: 48,354 kg (106,602 lb). Empty Mass: 2,948 kg (6,499 lb). Motor: 1 x MB-3-1. Thrust (vac): 760.643 kN (170,999 lbf). Isp: 285 sec. Burn time: 164 sec. Length: 18.41 m (60.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta D. Gross Mass: 2,693 kg (5,937 lb). Empty Mass: 545 kg (1,201 lb). Motor: 1 x AJ10-118D. Thrust (vac): 33.695 kN (7,575 lbf). Isp: 278 sec. Burn time: 170 sec. Length: 5.58 m (18.30 ft). Diameter: 0.84 m (2.75 ft). Propellants: Nitric acid/UDMH.

• Stage3: 1 x Altair 2. Gross Mass: 275 kg (606 lb). Empty Mass: 37 kg (81 lb). Motor: 1 x X-258. Thrust (vac): 22.241 kN (5,000 lbf). Isp: 266 sec. Burn time: 28 sec. Length: 2.53 m (8.30 ft). Diameter: 0.64 m (2.09 ft). Propellants: Solid.

• Stage1: 1 x Thor DM-21. Gross Mass: 48,354 kg (106,602 lb). Empty Mass: 2,948 kg (6,499 lb). Motor: 1 x MB-3-1. Thrust (vac): 760.643 kN (170,999 lbf). Isp: 285 sec. Burn time: 164 sec. Length: 18.41 m (60.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta D. Gross Mass: 2,693 kg (5,937 lb). Empty Mass: 545 kg (1,201 lb). Motor: 1 x AJ10-118D. Thrust (vac): 33.695 kN (7,575 lbf). Isp: 278 sec. Burn time: 170 sec. Length: 5.58 m (18.30 ft). Diameter: 0.84 m (2.75 ft). Propellants: Nitric acid/UDMH.

• Stage3: 1 x Altair 1. Gross Mass: 238 kg (524 lb). Empty Mass: 30 kg (66 lb). Motor: 1 x X-248. Thrust (vac): 12.450 kN (2,799 lbf). Isp: 256 sec. Burn time: 38 sec. Length: 1.83 m (6.00 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.

Launches: 2. First Launch Date: 1964-08-19. Last Launch Date: 1965-04-06. LEO Payload: 450 kg (990 lb). Payload: 104 kg (229 lb). to a: Geosynchronous transfer trajectory. Apogee: 40,000 km (24,000 mi). Associated Spacecraft: Intelsat 1, Syncom. Liftoff Thrust: 1,571.000 kN (353,174 lbf). Total Mass: 63,966 kg (141,020 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 32.00 m (104.00 ft). Flyaway Unit Cost $: 12.720 million. in: 1985 unit dollars.

• Stage0: 3 x Castor 1. Gross Mass: 3,852 kg (8,492 lb). Empty Mass: 535 kg (1,179 lb). Motor: 1 x M33-20-4. Thrust (vac): 286.001 kN (64,296 lbf). Isp: 247 sec. Burn time: 27 sec. Length: 5.92 m (19.42 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor TA. Gross Mass: 49,442 kg (109,000 lb). Empty Mass: 3,175 kg (6,999 lb). Motor: 1 x MB-3-3. Thrust (vac): 866.710 kN (194,844 lbf). Isp: 290 sec. Burn time: 150 sec. Length: 18.41 m (60.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta D. Gross Mass: 2,693 kg (5,937 lb). Empty Mass: 545 kg (1,201 lb). Motor: 1 x AJ10-118D. Thrust (vac): 33.695 kN (7,575 lbf). Isp: 278 sec. Burn time: 170 sec. Length: 5.58 m (18.30 ft). Diameter: 0.84 m (2.75 ft). Propellants: Nitric acid/UDMH.

• Stage3: 1 x Altair 2. Gross Mass: 275 kg (606 lb). Empty Mass: 37 kg (81 lb). Motor: 1 x X-258. Thrust (vac): 22.241 kN (5,000 lbf). Isp: 266 sec. Burn time: 28 sec. Length: 2.53 m (8.30 ft). Diameter: 0.64 m (2.09 ft). Propellants: Solid.

LEO Payload: 540 kg (1,190 lb). Payload: 150 kg (330 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: GEOS, HEOS, IMP, Intelsat 2, Isis, Pioneer 6-7-8-9-E, Tiros, TOS, TTS. Liftoff Thrust: 1,452.900 kN (326,625 lbf). Total Mass: 69,023 kg (152,169 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 31.00 m (101.00 ft). Flyaway Unit Cost $: 13.930 million. in: 1985 unit dollars.

• Stage0: 3 x Castor 1. Gross Mass: 3,852 kg (8,492 lb). Empty Mass: 535 kg (1,179 lb). Motor: 1 x M33-20-4. Thrust (vac): 286.001 kN (64,296 lbf). Isp: 247 sec. Burn time: 27 sec. Length: 5.92 m (19.42 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor TA. Gross Mass: 49,442 kg (109,000 lb). Empty Mass: 3,175 kg (6,999 lb). Motor: 1 x MB-3-3. Thrust (vac): 866.710 kN (194,844 lbf). Isp: 290 sec. Burn time: 150 sec. Length: 18.41 m (60.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta E. Gross Mass: 6,009 kg (13,247 lb). Empty Mass: 785 kg (1,730 lb). Motor: 1 x AJ10-118E. Thrust (vac): 35.098 kN (7,890 lbf). Isp: 278 sec. Burn time: 400 sec. Length: 6.28 m (20.60 ft). Diameter: 1.40 m (4.50 ft). Propellants: Nitric acid/UDMH.

• Stage3: 1 x Altair 2. Gross Mass: 275 kg (606 lb). Empty Mass: 37 kg (81 lb). Motor: 1 x X-258. Thrust (vac): 22.241 kN (5,000 lbf). Isp: 266 sec. Burn time: 28 sec. Length: 2.53 m (8.30 ft). Diameter: 0.64 m (2.09 ft). Propellants: Solid.

• Stage0: 3 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor TA. Gross Mass: 49,442 kg (109,000 lb). Empty Mass: 3,175 kg (6,999 lb). Motor: 1 x MB-3-3. Thrust (vac): 866.710 kN (194,844 lbf). Isp: 290 sec. Burn time: 150 sec. Length: 18.41 m (60.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta E. Gross Mass: 6,009 kg (13,247 lb). Empty Mass: 785 kg (1,730 lb). Motor: 1 x AJ10-118E. Thrust (vac): 35.098 kN (7,890 lbf). Isp: 278 sec. Burn time: 400 sec. Length: 6.28 m (20.60 ft). Diameter: 1.40 m (4.50 ft). Propellants: Nitric acid/UDMH.

• Stage3: 1 x FW-4D. Gross Mass: 300 kg (660 lb). Empty Mass: 25 kg (55 lb). Motor: 1 x FW-4D. Thrust (vac): 24.997 kN (5,620 lbf). Isp: 287 sec. Burn time: 31 sec. Length: 1.48 m (4.85 ft). Diameter: 0.50 m (1.64 ft). Propellants: Solid.

Launches: 2. First Launch Date: 1966-12-14. Last Launch Date: 1967-09-07. Apogee: 400 km (240 mi). Associated Spacecraft: Biosatellite. Liftoff Thrust: 765.100 kN (172,001 lbf). Total Mass: 55,451 kg (122,248 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 30.00 m (98.00 ft). Flyaway Unit Cost $: 10.150 million. in: 1985 unit dollars.

• Stage0: 3 x Castor 1. Gross Mass: 3,852 kg (8,492 lb). Empty Mass: 535 kg (1,179 lb). Motor: 1 x M33-20-4. Thrust (vac): 286.001 kN (64,296 lbf). Isp: 247 sec. Burn time: 27 sec. Length: 5.92 m (19.42 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor TA. Gross Mass: 49,442 kg (109,000 lb). Empty Mass: 3,175 kg (6,999 lb). Motor: 1 x MB-3-3. Thrust (vac): 866.710 kN (194,844 lbf). Isp: 290 sec. Burn time: 150 sec. Length: 18.41 m (60.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta E. Gross Mass: 6,009 kg (13,247 lb). Empty Mass: 785 kg (1,730 lb). Motor: 1 x AJ10-118E. Thrust (vac): 35.098 kN (7,890 lbf). Isp: 278 sec. Burn time: 400 sec. Length: 6.28 m (20.60 ft). Diameter: 1.40 m (4.50 ft). Propellants: Nitric acid/UDMH.

Launches: 1. First Launch Date: 1968-07-04. Last Launch Date: 1968-07-04. LEO Payload: 260 kg (570 lb). Payload: 263 kg (579 lb). to a: Geosynchronous transfer trajectory. Apogee: 6,000 km (3,700 mi). Associated Spacecraft: RAE. Liftoff Thrust: 1,452.900 kN (326,625 lbf). Total Mass: 69,497 kg (153,214 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 31.00 m (101.00 ft). Flyaway Unit Cost $: 16.660 million. in: 1985 unit dollars.

• Stage0: 3 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor TA. Gross Mass: 49,442 kg (109,000 lb). Empty Mass: 3,175 kg (6,999 lb). Motor: 1 x MB-3-3. Thrust (vac): 866.710 kN (194,844 lbf). Isp: 290 sec. Burn time: 150 sec. Length: 18.41 m (60.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta E. Gross Mass: 6,009 kg (13,247 lb). Empty Mass: 785 kg (1,730 lb). Motor: 1 x AJ10-118E. Thrust (vac): 35.098 kN (7,890 lbf). Isp: 278 sec. Burn time: 400 sec. Length: 6.28 m (20.60 ft). Diameter: 1.40 m (4.50 ft). Propellants: Nitric acid/UDMH.

• Stage3: 1 x Burner 2. Gross Mass: 774 kg (1,706 lb). Empty Mass: 116 kg (255 lb). Motor: 1 x Star 37. Thrust (vac): 43.551 kN (9,791 lbf). Isp: 285 sec. Burn time: 42 sec. Length: 0.84 m (2.75 ft). Diameter: 0.66 m (2.16 ft). Propellants: Solid.

Launches: 2. Failures: 1. First Launch Date: 1969-08-27. Last Launch Date: 1972-01-31. LEO Payload: 300 kg (660 lb). Payload: 300 kg (660 lb). to a: geosynchronous transfer orbit trajectory. Apogee: 400,000 km (240,000 mi). Associated Spacecraft: HEOS, Pioneer 6-7-8-9-E, TETR. Liftoff Thrust: 1,452.900 kN (326,625 lbf). Total Mass: 89,935 kg (198,272 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 35.00 m (114.00 ft). Flyaway Unit Cost $: 16.540 million. in: 1985 unit dollars.

• Stage0: 3 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor LT. Gross Mass: 70,354 kg (155,104 lb). Empty Mass: 3,715 kg (8,190 lb). Motor: 1 x MB-3-3. Thrust (vac): 866.710 kN (194,844 lbf). Isp: 290 sec. Burn time: 215 sec. Length: 21.43 m (70.30 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta E. Gross Mass: 6,009 kg (13,247 lb). Empty Mass: 785 kg (1,730 lb). Motor: 1 x AJ10-118E. Thrust (vac): 35.098 kN (7,890 lbf). Isp: 278 sec. Burn time: 400 sec. Length: 6.28 m (20.60 ft). Diameter: 1.40 m (4.50 ft). Propellants: Nitric acid/UDMH.

• Stage3: 1 x FW-4D. Gross Mass: 300 kg (660 lb). Empty Mass: 25 kg (55 lb). Motor: 1 x FW-4D. Thrust (vac): 24.997 kN (5,620 lbf). Isp: 287 sec. Burn time: 31 sec. Length: 1.48 m (4.85 ft). Diameter: 0.50 m (1.64 ft). Propellants: Solid.

LEO Payload: 355 kg (782 lb). Payload: 355 kg (782 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: IMP, Intelsat 3, NATO 1. Liftoff Thrust: 2,140.700 kN (481,249 lbf). Total Mass: 103,681 kg (228,577 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 34.00 m (111.00 ft). Flyaway Unit Cost $: 22.300 million. in: 1985 unit dollars.

• Stage0: 3 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor LT. Gross Mass: 70,354 kg (155,104 lb). Empty Mass: 3,715 kg (8,190 lb). Motor: 1 x MB-3-3. Thrust (vac): 866.710 kN (194,844 lbf). Isp: 290 sec. Burn time: 215 sec. Length: 21.43 m (70.30 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta E. Gross Mass: 6,009 kg (13,247 lb). Empty Mass: 785 kg (1,730 lb). Motor: 1 x AJ10-118E. Thrust (vac): 35.098 kN (7,890 lbf). Isp: 278 sec. Burn time: 400 sec. Length: 6.28 m (20.60 ft). Diameter: 1.40 m (4.50 ft). Propellants: Nitric acid/UDMH.

• Stage3: 1 x Star 37D. Gross Mass: 718 kg (1,582 lb). Empty Mass: 64 kg (141 lb). Motor: 1 x Star 37D. Thrust (vac): 45.000 kN (10,116 lbf). Length: 1.50 m (4.90 ft). Diameter: 0.94 m (3.08 ft). Propellants: Solid.

• Stage0: 6 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor LT. Gross Mass: 70,354 kg (155,104 lb). Empty Mass: 3,715 kg (8,190 lb). Motor: 1 x MB-3-3. Thrust (vac): 866.710 kN (194,844 lbf). Isp: 290 sec. Burn time: 215 sec. Length: 21.43 m (70.30 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta E. Gross Mass: 6,009 kg (13,247 lb). Empty Mass: 785 kg (1,730 lb). Motor: 1 x AJ10-118E. Thrust (vac): 35.098 kN (7,890 lbf). Isp: 278 sec. Burn time: 400 sec. Length: 6.28 m (20.60 ft). Diameter: 1.40 m (4.50 ft). Propellants: Nitric acid/UDMH.

• Stage3: 1 x Burner 2. Gross Mass: 774 kg (1,706 lb). Empty Mass: 116 kg (255 lb). Motor: 1 x Star 37. Thrust (vac): 43.551 kN (9,791 lbf). Isp: 285 sec. Burn time: 42 sec. Length: 0.84 m (2.75 ft). Diameter: 0.66 m (2.16 ft). Propellants: Solid.

Associated Spacecraft: Biosatellite, ITOS, Oscar, OSO, PAC, TD-1A, TETR, TOS. Liftoff Thrust: 1,590.000 kN (357,440 lbf). Total Mass: 90,000 kg (198,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 33.00 m (108.00 ft). Flyaway Unit Cost $: 18.820 million. in: 1985 unit dollars.

• Stage0: 3 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor LT. Gross Mass: 70,354 kg (155,104 lb). Empty Mass: 3,715 kg (8,190 lb). Motor: 1 x MB-3-3. Thrust (vac): 866.710 kN (194,844 lbf). Isp: 290 sec. Burn time: 215 sec. Length: 21.43 m (70.30 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta E. Gross Mass: 6,009 kg (13,247 lb). Empty Mass: 785 kg (1,730 lb). Motor: 1 x AJ10-118E. Thrust (vac): 35.098 kN (7,890 lbf). Isp: 278 sec. Burn time: 400 sec. Length: 6.28 m (20.60 ft). Diameter: 1.40 m (4.50 ft). Propellants: Nitric acid/UDMH.

• Stage0: 6 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor LT. Gross Mass: 70,354 kg (155,104 lb). Empty Mass: 3,715 kg (8,190 lb). Motor: 1 x MB-3-3. Thrust (vac): 866.710 kN (194,844 lbf). Isp: 290 sec. Burn time: 215 sec. Length: 21.43 m (70.30 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta E. Gross Mass: 6,009 kg (13,247 lb). Empty Mass: 785 kg (1,730 lb). Motor: 1 x AJ10-118E. Thrust (vac): 35.098 kN (7,890 lbf). Isp: 278 sec. Burn time: 400 sec. Length: 6.28 m (20.60 ft). Diameter: 1.40 m (4.50 ft). Propellants: Nitric acid/UDMH.

Manufacturer: Mitsubishi. Launches: 9. First Launch Date: 1986-08-12. Last Launch Date: 1992-02-11. LEO Payload: 3,200 kg (7,000 lb). to: 185 km Orbit. Payload: 1,100 kg (2,400 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: AS 3000, CS-3, Debut, EGS, ETS, GMS, JERS, MABES, Marine Observation Satellite, Oscar. Liftoff Thrust: 2,131.800 kN (479,248 lbf). Total Mass: 142,260 kg (313,620 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 42.00 m (137.00 ft). Launch Price $: 90.000 million. in: 1990 price dollars.

• Stage0: 9 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x H-1-1. Gross Mass: 85,800 kg (189,100 lb). Empty Mass: 4,400 kg (9,700 lb). Motor: 1 x MB-3-3. Thrust (vac): 866.710 kN (194,844 lbf). Isp: 290 sec. Burn time: 270 sec. Length: 22.00 m (72.00 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x LE-5. Gross Mass: 10,600 kg (23,300 lb). Empty Mass: 1,800 kg (3,900 lb). Motor: 1 x LE-5. Thrust (vac): 102.900 kN (23,133 lbf). Isp: 450 sec. Burn time: 370 sec. Length: 10.32 m (33.85 ft). Diameter: 2.49 m (8.16 ft). Propellants: Lox/LH2.

• Stage3: 1 x UM-129A. Gross Mass: 2,200 kg (4,800 lb). Empty Mass: 360 kg (790 lb). Motor: 1 x H-1-3. Thrust (vac): 77.400 kN (17,400 lbf). Isp: 291 sec. Burn time: 68 sec. Length: 2.34 m (7.67 ft). Diameter: 1.34 m (4.39 ft). Propellants: Solid.

• Stage0: 9 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x H-1-1. Gross Mass: 85,800 kg (189,100 lb). Empty Mass: 4,400 kg (9,700 lb). Motor: 1 x MB-3-3. Thrust (vac): 866.710 kN (194,844 lbf). Isp: 290 sec. Burn time: 270 sec. Length: 22.00 m (72.00 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x LE-5. Gross Mass: 10,600 kg (23,300 lb). Empty Mass: 1,800 kg (3,900 lb). Motor: 1 x LE-5. Thrust (vac): 102.900 kN (23,133 lbf). Isp: 450 sec. Burn time: 370 sec. Length: 10.32 m (33.85 ft). Diameter: 2.49 m (8.16 ft). Propellants: Lox/LH2.

• Stage0: 9 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x H-1-1. Gross Mass: 85,800 kg (189,100 lb). Empty Mass: 4,400 kg (9,700 lb). Motor: 1 x MB-3-3. Thrust (vac): 866.710 kN (194,844 lbf). Isp: 290 sec. Burn time: 270 sec. Length: 22.00 m (72.00 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x LE-5. Gross Mass: 10,600 kg (23,300 lb). Empty Mass: 1,800 kg (3,900 lb). Motor: 1 x LE-5. Thrust (vac): 102.900 kN (23,133 lbf). Isp: 450 sec. Burn time: 370 sec. Length: 10.32 m (33.85 ft). Diameter: 2.49 m (8.16 ft). Propellants: Lox/LH2.

• Stage3: 1 x UM-129A. Gross Mass: 2,200 kg (4,800 lb). Empty Mass: 360 kg (790 lb). Motor: 1 x H-1-3. Thrust (vac): 77.400 kN (17,400 lbf). Isp: 291 sec. Burn time: 68 sec. Length: 2.34 m (7.67 ft). Diameter: 1.34 m (4.39 ft). Propellants: Solid.

Manufacturer: Mitsubishi. Launches: 7. Failures: 1. First Launch Date: 1975-09-09. Last Launch Date: 1982-09-03. LEO Payload: 1,200 kg (2,600 lb). to: 185 km Orbit. Payload: 360 kg (790 lb). to a: Geosynchronous transfer trajectory. Apogee: 40,000 km (24,000 mi). Associated Spacecraft: Ayame, ETS, JISS. Liftoff Thrust: 2,287.500 kN (514,250 lbf). Total Mass: 131,330 kg (289,530 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 34.00 m (111.00 ft). Flyaway Unit Cost $: 23.010 million. in: 1985 unit dollars.

• Stage0: 9 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor ELT. Gross Mass: 84,067 kg (185,336 lb). Empty Mass: 4,059 kg (8,948 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.208 kN (231,600 lbf). Isp: 296 sec. Burn time: 222 sec. Length: 22.40 m (73.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta E. Gross Mass: 6,009 kg (13,247 lb). Empty Mass: 785 kg (1,730 lb). Motor: 1 x AJ10-118E. Thrust (vac): 35.098 kN (7,890 lbf). Isp: 278 sec. Burn time: 400 sec. Length: 6.28 m (20.60 ft). Diameter: 1.40 m (4.50 ft). Propellants: Nitric acid/UDMH.

Manufacturer: Mitsubishi. Launches: 8. First Launch Date: 1981-02-11. Last Launch Date: 1987-02-19. LEO Payload: 2,000 kg (4,400 lb). to: 185 km Orbit. Payload: 730 kg (1,600 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: AS 3000, CS-2, ETS, GMS, Marine Observation Satellite. Liftoff Thrust: 2,287.500 kN (514,250 lbf). Total Mass: 132,690 kg (292,530 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 35.00 m (114.00 ft). Flyaway Unit Cost $: 26.490 million. in: 1985 unit dollars.

• Stage0: 9 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x H-1-1. Gross Mass: 85,800 kg (189,100 lb). Empty Mass: 4,400 kg (9,700 lb). Motor: 1 x MB-3-3. Thrust (vac): 866.710 kN (194,844 lbf). Isp: 290 sec. Burn time: 270 sec. Length: 22.00 m (72.00 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta F. Gross Mass: 5,629 kg (12,409 lb). Empty Mass: 784 kg (1,728 lb). Motor: 1 x AJ10-118F. Thrust (vac): 41.364 kN (9,299 lbf). Isp: 280 sec. Burn time: 335 sec. Length: 6.28 m (20.60 ft). Diameter: 1.40 m (4.50 ft). Propellants: Nitric acid/UDMH.

• Stage3: 1 x Star 37E. Gross Mass: 1,123 kg (2,475 lb). Empty Mass: 83 kg (182 lb). Motor: 1 x Star 37E. Thrust (vac): 68.000 kN (15,287 lbf). Burn time: 42 sec. Length: 1.70 m (5.50 ft). Diameter: 0.94 m (3.08 ft). Propellants: Solid.

• Stage0: 9 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor ELT. Gross Mass: 84,067 kg (185,336 lb). Empty Mass: 4,059 kg (8,948 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.208 kN (231,600 lbf). Isp: 296 sec. Burn time: 222 sec. Length: 22.40 m (73.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta F. Gross Mass: 5,629 kg (12,409 lb). Empty Mass: 784 kg (1,728 lb). Motor: 1 x AJ10-118F. Thrust (vac): 41.364 kN (9,299 lbf). Isp: 280 sec. Burn time: 335 sec. Length: 6.28 m (20.60 ft). Diameter: 1.40 m (4.50 ft). Propellants: Nitric acid/UDMH.

• Stage3: 1 x Burner 2. Gross Mass: 774 kg (1,706 lb). Empty Mass: 116 kg (255 lb). Motor: 1 x Star 37. Thrust (vac): 43.551 kN (9,791 lbf). Isp: 285 sec. Burn time: 42 sec. Length: 0.84 m (2.75 ft). Diameter: 0.66 m (2.16 ft). Propellants: Solid.

Payload: 635 kg (1,399 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: ITOS, Landsat 1-2-3, Nimbus, Oscar. Liftoff Thrust: 2,140.700 kN (481,249 lbf). Total Mass: 116,573 kg (256,999 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 34.00 m (111.00 ft). Flyaway Unit Cost $: 25.330 million. in: 1985 unit dollars. Version:

Delta 0300. Status: Retired 1973.

Three stage vehicle consisting of 3 x Castor 2 + 1 x LT Thor DSV-2L-1C + 1 x DSV-3N-4

Launches: 3. Failures: 1. First Launch Date: 1972-10-15. Last Launch Date: 1973-11-06. Apogee: 1,500 km (900 mi). Liftoff Thrust: 1,590.000 kN (357,440 lbf). Total Mass: 90,100 kg (198,600 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 34.00 m (111.00 ft).

• Stage0: 3 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor LT. Gross Mass: 70,354 kg (155,104 lb). Empty Mass: 3,715 kg (8,190 lb). Motor: 1 x MB-3-3. Thrust (vac): 866.710 kN (194,844 lbf). Isp: 290 sec. Burn time: 215 sec. Length: 21.43 m (70.30 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta F. Gross Mass: 5,629 kg (12,409 lb). Empty Mass: 784 kg (1,728 lb). Motor: 1 x AJ10-118F. Thrust (vac): 41.364 kN (9,299 lbf). Isp: 280 sec. Burn time: 335 sec. Length: 6.28 m (20.60 ft). Diameter: 1.40 m (4.50 ft). Propellants: Nitric acid/UDMH.

• Stage0: 9 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor LT. Gross Mass: 70,354 kg (155,104 lb). Empty Mass: 3,715 kg (8,190 lb). Motor: 1 x MB-3-3. Thrust (vac): 866.710 kN (194,844 lbf). Isp: 290 sec. Burn time: 215 sec. Length: 21.43 m (70.30 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta F. Gross Mass: 5,629 kg (12,409 lb). Empty Mass: 784 kg (1,728 lb). Motor: 1 x AJ10-118F. Thrust (vac): 41.364 kN (9,299 lbf). Isp: 280 sec. Burn time: 335 sec. Length: 6.28 m (20.60 ft). Diameter: 1.40 m (4.50 ft). Propellants: Nitric acid/UDMH.

• Stage3: 1 x Burner 2. Gross Mass: 774 kg (1,706 lb). Empty Mass: 116 kg (255 lb). Motor: 1 x Star 37. Thrust (vac): 43.551 kN (9,791 lbf). Isp: 285 sec. Burn time: 42 sec. Length: 0.84 m (2.75 ft). Diameter: 0.66 m (2.16 ft). Propellants: Solid.

Associated Spacecraft: AE, Geos, HS 333, IMP, OSO, RAE. Liftoff Thrust: 2,287.500 kN (514,250 lbf). Total Mass: 130,286 kg (287,231 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 35.00 m (114.00 ft). Flyaway Unit Cost $: 26.490 million. in: 1985 unit dollars. Version:

Delta 1410. Status: Retired 1975.

Three stage vehicle consisting of 4 x Castor 2 + 1 x ELT Thor/MB-3 + 1 x Delta P /TR-201

Launches: 1. First Launch Date: 1975-04-09. Last Launch Date: 1975-04-09. Apogee: 900 km (550 mi). Liftoff Thrust: 1,863.000 kN (418,819 lbf). Total Mass: 110,000 kg (240,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 35.00 m (114.00 ft).

• Stage0: 4 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor ELT. Gross Mass: 84,067 kg (185,336 lb). Empty Mass: 4,059 kg (8,948 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.208 kN (231,600 lbf). Isp: 296 sec. Burn time: 222 sec. Length: 22.40 m (73.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta P. Gross Mass: 5,434 kg (11,979 lb). Empty Mass: 820 kg (1,800 lb). Motor: 1 x TR-201. Thrust (vac): 41.923 kN (9,425 lbf). Isp: 301 sec. Burn time: 322 sec. Length: 5.97 m (19.58 ft). Diameter: 1.38 m (4.52 ft). Propellants: N2O4/Aerozine-50.

• Stage0: 6 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor ELT. Gross Mass: 84,067 kg (185,336 lb). Empty Mass: 4,059 kg (8,948 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.208 kN (231,600 lbf). Isp: 296 sec. Burn time: 222 sec. Length: 22.40 m (73.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta F. Gross Mass: 5,629 kg (12,409 lb). Empty Mass: 784 kg (1,728 lb). Motor: 1 x AJ10-118F. Thrust (vac): 41.364 kN (9,299 lbf). Isp: 280 sec. Burn time: 335 sec. Length: 6.28 m (20.60 ft). Diameter: 1.40 m (4.50 ft). Propellants: Nitric acid/UDMH.

• Stage3: 1 x Star 37C. Gross Mass: 1,048 kg (2,310 lb). Empty Mass: 83 kg (182 lb). Motor: 1 x Star 37C. Thrust (vac): 45.000 kN (10,116 lbf). Length: 1.50 m (4.90 ft). Diameter: 0.94 m (3.08 ft). Propellants: Solid.

• Stage0: 9 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor ELT. Gross Mass: 84,067 kg (185,336 lb). Empty Mass: 4,059 kg (8,948 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.208 kN (231,600 lbf). Isp: 296 sec. Burn time: 222 sec. Length: 22.40 m (73.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta F. Gross Mass: 5,629 kg (12,409 lb). Empty Mass: 784 kg (1,728 lb). Motor: 1 x AJ10-118F. Thrust (vac): 41.364 kN (9,299 lbf). Isp: 280 sec. Burn time: 335 sec. Length: 6.28 m (20.60 ft). Diameter: 1.40 m (4.50 ft). Propellants: Nitric acid/UDMH.

• Stage0: 9 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor ELT. Gross Mass: 84,067 kg (185,336 lb). Empty Mass: 4,059 kg (8,948 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.208 kN (231,600 lbf). Isp: 296 sec. Burn time: 222 sec. Length: 22.40 m (73.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta F. Gross Mass: 5,629 kg (12,409 lb). Empty Mass: 784 kg (1,728 lb). Motor: 1 x AJ10-118F. Thrust (vac): 41.364 kN (9,299 lbf). Isp: 280 sec. Burn time: 335 sec. Length: 6.28 m (20.60 ft). Diameter: 1.40 m (4.50 ft). Propellants: Nitric acid/UDMH.

• Stage0: 9 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor ELT. Gross Mass: 84,067 kg (185,336 lb). Empty Mass: 4,059 kg (8,948 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.208 kN (231,600 lbf). Isp: 296 sec. Burn time: 222 sec. Length: 22.40 m (73.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta F. Gross Mass: 5,629 kg (12,409 lb). Empty Mass: 784 kg (1,728 lb). Motor: 1 x AJ10-118F. Thrust (vac): 41.364 kN (9,299 lbf). Isp: 280 sec. Burn time: 335 sec. Length: 6.28 m (20.60 ft). Diameter: 1.40 m (4.50 ft). Propellants: Nitric acid/UDMH.

• Stage3: 1 x Star 37D. Gross Mass: 718 kg (1,582 lb). Empty Mass: 64 kg (141 lb). Motor: 1 x Star 37D. Thrust (vac): 45.000 kN (10,116 lbf). Length: 1.50 m (4.90 ft). Diameter: 0.94 m (3.08 ft). Propellants: Solid.

• Stage0: 9 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor ELT. Gross Mass: 84,067 kg (185,336 lb). Empty Mass: 4,059 kg (8,948 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.208 kN (231,600 lbf). Isp: 296 sec. Burn time: 222 sec. Length: 22.40 m (73.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta P. Gross Mass: 5,434 kg (11,979 lb). Empty Mass: 820 kg (1,800 lb). Motor: 1 x TR-201. Thrust (vac): 41.923 kN (9,425 lbf). Isp: 301 sec. Burn time: 322 sec. Length: 5.97 m (19.58 ft). Diameter: 1.38 m (4.52 ft). Propellants: N2O4/Aerozine-50.

• Stage3: 1 x Burner 2. Gross Mass: 774 kg (1,706 lb). Empty Mass: 116 kg (255 lb). Motor: 1 x Star 37. Thrust (vac): 43.551 kN (9,791 lbf). Isp: 285 sec. Burn time: 42 sec. Length: 0.84 m (2.75 ft). Diameter: 0.66 m (2.16 ft). Propellants: Solid.

Payload: 724 kg (1,596 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: AE, CAMEO, COS, CS-1, CTS, ESA-Geos, GMS, GOES, HS 333, Intasat, ISEE, ITOS, IUE, Lageos, Landsat 1-2-3, Marisat, Meteosat, Microsat SSTL, NATO 3, Nimbus, Oscar, PIX, SCATHA, Sirio, Skynet, SME, SMS, Spacebus 100, Symphonie, Yuri. Liftoff Thrust: 2,287.500 kN (514,250 lbf). Total Mass: 130,392 kg (287,465 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 35.00 m (114.00 ft). Flyaway Unit Cost $: 28.520 million. in: 1985 unit dollars. Version:

Delta 2310. Status: Retired 1981.

Three stage vehicle consisting of 3 x Castor 2 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201

Launches: 3. First Launch Date: 1974-11-15. Last Launch Date: 1981-10-06. Apogee: 1,500 km (900 mi). Liftoff Thrust: 1,737.000 kN (390,493 lbf). Total Mass: 131,000 kg (288,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 35.00 m (114.00 ft).

• Stage0: 3 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor ELT. Gross Mass: 84,067 kg (185,336 lb). Empty Mass: 4,059 kg (8,948 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.208 kN (231,600 lbf). Isp: 296 sec. Burn time: 222 sec. Length: 22.40 m (73.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta P. Gross Mass: 5,434 kg (11,979 lb). Empty Mass: 820 kg (1,800 lb). Motor: 1 x TR-201. Thrust (vac): 41.923 kN (9,425 lbf). Isp: 301 sec. Burn time: 322 sec. Length: 5.97 m (19.58 ft). Diameter: 1.38 m (4.52 ft). Propellants: N2O4/Aerozine-50.

• Stage0: 3 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor ELT. Gross Mass: 84,067 kg (185,336 lb). Empty Mass: 4,059 kg (8,948 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.208 kN (231,600 lbf). Isp: 296 sec. Burn time: 222 sec. Length: 22.40 m (73.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta P. Gross Mass: 5,434 kg (11,979 lb). Empty Mass: 820 kg (1,800 lb). Motor: 1 x TR-201. Thrust (vac): 41.923 kN (9,425 lbf). Isp: 301 sec. Burn time: 322 sec. Length: 5.97 m (19.58 ft). Diameter: 1.38 m (4.52 ft). Propellants: N2O4/Aerozine-50.

• Stage3: 1 x Star 37D. Gross Mass: 718 kg (1,582 lb). Empty Mass: 64 kg (141 lb). Motor: 1 x Star 37D. Thrust (vac): 45.000 kN (10,116 lbf). Length: 1.50 m (4.90 ft). Diameter: 0.94 m (3.08 ft). Propellants: Solid.

• Stage0: 9 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor ELT. Gross Mass: 84,067 kg (185,336 lb). Empty Mass: 4,059 kg (8,948 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.208 kN (231,600 lbf). Isp: 296 sec. Burn time: 222 sec. Length: 22.40 m (73.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta P. Gross Mass: 5,434 kg (11,979 lb). Empty Mass: 820 kg (1,800 lb). Motor: 1 x TR-201. Thrust (vac): 41.923 kN (9,425 lbf). Isp: 301 sec. Burn time: 322 sec. Length: 5.97 m (19.58 ft). Diameter: 1.38 m (4.52 ft). Propellants: N2O4/Aerozine-50.

• Stage0: 9 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor ELT. Gross Mass: 84,067 kg (185,336 lb). Empty Mass: 4,059 kg (8,948 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.208 kN (231,600 lbf). Isp: 296 sec. Burn time: 222 sec. Length: 22.40 m (73.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta P. Gross Mass: 5,434 kg (11,979 lb). Empty Mass: 820 kg (1,800 lb). Motor: 1 x TR-201. Thrust (vac): 41.923 kN (9,425 lbf). Isp: 301 sec. Burn time: 322 sec. Length: 5.97 m (19.58 ft). Diameter: 1.38 m (4.52 ft). Propellants: N2O4/Aerozine-50.

• Stage3: 1 x Star 37D. Gross Mass: 718 kg (1,582 lb). Empty Mass: 64 kg (141 lb). Motor: 1 x Star 37D. Thrust (vac): 45.000 kN (10,116 lbf). Length: 1.50 m (4.90 ft). Diameter: 0.94 m (3.08 ft). Propellants: Solid.

• Stage0: 9 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Motor: 1 x TX-354-3. Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Length: 6.04 m (19.81 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor RS27. Gross Mass: 84,368 kg (185,999 lb). Empty Mass: 4,360 kg (9,610 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.218 kN (231,602 lbf). Isp: 296 sec. Burn time: 223 sec. Length: 22.37 m (73.39 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta P. Gross Mass: 5,434 kg (11,979 lb). Empty Mass: 820 kg (1,800 lb). Motor: 1 x TR-201. Thrust (vac): 41.923 kN (9,425 lbf). Isp: 301 sec. Burn time: 322 sec. Length: 5.97 m (19.58 ft). Diameter: 1.38 m (4.52 ft). Propellants: N2O4/Aerozine-50.

• Stage3: 1 x Burner 2. Gross Mass: 774 kg (1,706 lb). Empty Mass: 116 kg (255 lb). Motor: 1 x Star 37. Thrust (vac): 43.551 kN (9,791 lbf). Isp: 285 sec. Burn time: 42 sec. Length: 0.84 m (2.75 ft). Diameter: 0.66 m (2.16 ft). Propellants: Solid.

Payload: 954 kg (2,103 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: AMPTE, Anik, AS 1000, AS 3000, Dynamics Explorer, ECS/OTS, Exosat, GOES, HS 376, Insat 1, IRAS, Landsat 4-5, Microsat SSTL, NATO 3, SDI, SMM. Liftoff Thrust: 3,046.200 kN (684,813 lbf). Total Mass: 185,382 kg (408,697 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 35.00 m (114.00 ft). Launch Price $: 16.300 million. in: 1977 price dollars. Version:

Delta 3910. Status: Retired 1988.

Three stage vehicle consisting of 9 x Castor 4 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201

Launches: 3. First Launch Date: 1980-02-14. Last Launch Date: 1988-02-08. Apogee: 1,000 km (600 mi). Liftoff Thrust: 3,188.000 kN (716,690 lbf). Total Mass: 190,000 kg (410,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 35.00 m (114.00 ft).

• Stage0: 9 x Castor 4. Gross Mass: 10,534 kg (23,223 lb). Empty Mass: 1,269 kg (2,797 lb). Motor: 1 x Castor 4. Thrust (vac): 407.211 kN (91,545 lbf). Isp: 261 sec. Burn time: 54 sec. Length: 9.07 m (29.75 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor RS27. Gross Mass: 84,368 kg (185,999 lb). Empty Mass: 4,360 kg (9,610 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.218 kN (231,602 lbf). Isp: 296 sec. Burn time: 223 sec. Length: 22.37 m (73.39 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta P. Gross Mass: 5,434 kg (11,979 lb). Empty Mass: 820 kg (1,800 lb). Motor: 1 x TR-201. Thrust (vac): 41.923 kN (9,425 lbf). Isp: 301 sec. Burn time: 322 sec. Length: 5.97 m (19.58 ft). Diameter: 1.38 m (4.52 ft). Propellants: N2O4/Aerozine-50.

• Stage0: 9 x Castor 4. Gross Mass: 10,534 kg (23,223 lb). Empty Mass: 1,269 kg (2,797 lb). Motor: 1 x Castor 4. Thrust (vac): 407.211 kN (91,545 lbf). Isp: 261 sec. Burn time: 54 sec. Length: 9.07 m (29.75 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor RS27. Gross Mass: 84,368 kg (185,999 lb). Empty Mass: 4,360 kg (9,610 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.218 kN (231,602 lbf). Isp: 296 sec. Burn time: 223 sec. Length: 22.37 m (73.39 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta P. Gross Mass: 5,434 kg (11,979 lb). Empty Mass: 820 kg (1,800 lb). Motor: 1 x TR-201. Thrust (vac): 41.923 kN (9,425 lbf). Isp: 301 sec. Burn time: 322 sec. Length: 5.97 m (19.58 ft). Diameter: 1.38 m (4.52 ft). Propellants: N2O4/Aerozine-50.

• Stage3: 1 x PAM-D. Gross Mass: 2,141 kg (4,720 lb). Empty Mass: 232 kg (511 lb). Motor: 1 x Star 48. Thrust (vac): 67.155 kN (15,097 lbf). Isp: 292 sec. Burn time: 88 sec. Length: 2.04 m (6.69 ft). Diameter: 1.24 m (4.06 ft). Propellants: Solid.

• Stage0: 9 x Castor 4. Gross Mass: 10,534 kg (23,223 lb). Empty Mass: 1,269 kg (2,797 lb). Motor: 1 x Castor 4. Thrust (vac): 407.211 kN (91,545 lbf). Isp: 261 sec. Burn time: 54 sec. Length: 9.07 m (29.75 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor RS27. Gross Mass: 84,368 kg (185,999 lb). Empty Mass: 4,360 kg (9,610 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.218 kN (231,602 lbf). Isp: 296 sec. Burn time: 223 sec. Length: 22.37 m (73.39 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta P. Gross Mass: 5,434 kg (11,979 lb). Empty Mass: 820 kg (1,800 lb). Motor: 1 x TR-201. Thrust (vac): 41.923 kN (9,425 lbf). Isp: 301 sec. Burn time: 322 sec. Length: 5.97 m (19.58 ft). Diameter: 1.38 m (4.52 ft). Propellants: N2O4/Aerozine-50.

• Stage3: 1 x Star 37N. Gross Mass: 623 kg (1,373 lb). Empty Mass: 64 kg (141 lb). Motor: 1 x Star 37N. Thrust (vac): 45.000 kN (10,116 lbf). Length: 1.70 m (5.50 ft). Diameter: 0.94 m (3.08 ft). Propellants: Solid.

• Stage0: 9 x Castor 4. Gross Mass: 10,534 kg (23,223 lb). Empty Mass: 1,269 kg (2,797 lb). Motor: 1 x Castor 4. Thrust (vac): 407.211 kN (91,545 lbf). Isp: 261 sec. Burn time: 54 sec. Length: 9.07 m (29.75 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor RS27. Gross Mass: 84,368 kg (185,999 lb). Empty Mass: 4,360 kg (9,610 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.218 kN (231,602 lbf). Isp: 296 sec. Burn time: 223 sec. Length: 22.37 m (73.39 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta P. Gross Mass: 5,434 kg (11,979 lb). Empty Mass: 820 kg (1,800 lb). Motor: 1 x TR-201. Thrust (vac): 41.923 kN (9,425 lbf). Isp: 301 sec. Burn time: 322 sec. Length: 5.97 m (19.58 ft). Diameter: 1.38 m (4.52 ft). Propellants: N2O4/Aerozine-50.

• Stage3: 1 x Burner 2. Gross Mass: 774 kg (1,706 lb). Empty Mass: 116 kg (255 lb). Motor: 1 x Star 37. Thrust (vac): 43.551 kN (9,791 lbf). Isp: 285 sec. Burn time: 42 sec. Length: 0.84 m (2.75 ft). Diameter: 0.66 m (2.16 ft). Propellants: Solid.

• Stage0: 9 x Castor 4. Gross Mass: 10,534 kg (23,223 lb). Empty Mass: 1,269 kg (2,797 lb). Motor: 1 x Castor 4. Thrust (vac): 407.211 kN (91,545 lbf). Isp: 261 sec. Burn time: 54 sec. Length: 9.07 m (29.75 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor RS27. Gross Mass: 84,368 kg (185,999 lb). Empty Mass: 4,360 kg (9,610 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.218 kN (231,602 lbf). Isp: 296 sec. Burn time: 223 sec. Length: 22.37 m (73.39 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage0: 9 x Castor 4. Gross Mass: 10,534 kg (23,223 lb). Empty Mass: 1,269 kg (2,797 lb). Motor: 1 x Castor 4. Thrust (vac): 407.211 kN (91,545 lbf). Isp: 261 sec. Burn time: 54 sec. Length: 9.07 m (29.75 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor RS27. Gross Mass: 84,368 kg (185,999 lb). Empty Mass: 4,360 kg (9,610 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.218 kN (231,602 lbf). Isp: 296 sec. Burn time: 223 sec. Length: 22.37 m (73.39 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage3: 1 x PAM-D. Gross Mass: 2,141 kg (4,720 lb). Empty Mass: 232 kg (511 lb). Motor: 1 x Star 48. Thrust (vac): 67.155 kN (15,097 lbf). Isp: 292 sec. Burn time: 88 sec. Length: 2.04 m (6.69 ft). Diameter: 1.24 m (4.06 ft). Propellants: Solid.

• Stage0: 9 x Castor 4. Gross Mass: 10,534 kg (23,223 lb). Empty Mass: 1,269 kg (2,797 lb). Motor: 1 x Castor 4. Thrust (vac): 407.211 kN (91,545 lbf). Isp: 261 sec. Burn time: 54 sec. Length: 9.07 m (29.75 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor RS27. Gross Mass: 84,368 kg (185,999 lb). Empty Mass: 4,360 kg (9,610 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.218 kN (231,602 lbf). Isp: 296 sec. Burn time: 223 sec. Length: 22.37 m (73.39 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage0: 9 x Castor 4. Gross Mass: 10,534 kg (23,223 lb). Empty Mass: 1,269 kg (2,797 lb). Motor: 1 x Castor 4. Thrust (vac): 407.211 kN (91,545 lbf). Isp: 261 sec. Burn time: 54 sec. Length: 9.07 m (29.75 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor RS27. Gross Mass: 84,368 kg (185,999 lb). Empty Mass: 4,360 kg (9,610 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.218 kN (231,602 lbf). Isp: 296 sec. Burn time: 223 sec. Length: 22.37 m (73.39 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage3: 1 x Star 37E. Gross Mass: 1,123 kg (2,475 lb). Empty Mass: 83 kg (182 lb). Motor: 1 x Star 37E. Thrust (vac): 68.000 kN (15,287 lbf). Burn time: 42 sec. Length: 1.70 m (5.50 ft). Diameter: 0.94 m (3.08 ft). Propellants: Solid.

LEO Payload: 3,451 kg (7,608 lb). to: 185 km Orbit. Payload: 1,283 kg (2,828 lb). to a: Geosynchronous transfer trajectory. Liftoff Thrust: 3,046.200 kN (684,813 lbf). Total Mass: 192,360 kg (424,080 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 36.00 m (118.00 ft). Flyaway Unit Cost $: 38.320 million. in: 1985 unit dollars. Version:

Delta 4000.

Delta 4925

Status: Out of production.

The Delta 4000 series used more powerful Castor 4A strap-ons, but the old Extended Long Tank core with MB-3 engine. Only two of these were launched.

LEO Payload: 3,400 kg (7,400 lb). to: 185 km Orbit. Payload: 1,200 kg (2,600 lb). to a: Geosynchronous transfer trajectory. Apogee: 40,000 km (24,000 mi). Associated Spacecraft: HS 376, Insat 1. Liftoff Thrust: 3,468.800 kN (779,817 lbf). Total Mass: 200,740 kg (442,550 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 34.00 m (111.00 ft). Flyaway Unit Cost $: 34.220 million. in: 1985 unit dollars.

• Stage0: 9 x Castor 4A. Gross Mass: 11,743 kg (25,888 lb). Empty Mass: 1,529 kg (3,370 lb). Motor: 1 x Castor 4A. Thrust (vac): 478.309 kN (107,528 lbf). Isp: 266 sec. Burn time: 56 sec. Length: 9.12 m (29.92 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor ELT. Gross Mass: 84,067 kg (185,336 lb). Empty Mass: 4,059 kg (8,948 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.208 kN (231,600 lbf). Isp: 296 sec. Burn time: 222 sec. Length: 22.40 m (73.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage0: 9 x Castor 4A. Gross Mass: 11,743 kg (25,888 lb). Empty Mass: 1,529 kg (3,370 lb). Motor: 1 x Castor 4A. Thrust (vac): 478.309 kN (107,528 lbf). Isp: 266 sec. Burn time: 56 sec. Length: 9.12 m (29.92 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor ELT. Gross Mass: 84,067 kg (185,336 lb). Empty Mass: 4,059 kg (8,948 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.208 kN (231,600 lbf). Isp: 296 sec. Burn time: 222 sec. Length: 22.40 m (73.40 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage3: 1 x PAM-D. Gross Mass: 2,141 kg (4,720 lb). Empty Mass: 232 kg (511 lb). Motor: 1 x Star 48. Thrust (vac): 67.155 kN (15,097 lbf). Isp: 292 sec. Burn time: 88 sec. Length: 2.04 m (6.69 ft). Diameter: 1.24 m (4.06 ft). Propellants: Solid.

LEO Payload: 3,848 kg (8,483 lb). to: 185 km Orbit. Payload: 1,405 kg (3,097 lb). to a: Geosynchronous transfer trajectory. Apogee: 1,000 km (600 mi). Associated Spacecraft: COBE. Liftoff Thrust: 3,468.900 kN (779,840 lbf). Total Mass: 201,580 kg (444,400 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 34.00 m (111.00 ft). Flyaway Unit Cost $: 34.220 million. in: 1985 unit dollars.

• Stage0: 9 x Castor 4A. Gross Mass: 11,743 kg (25,888 lb). Empty Mass: 1,529 kg (3,370 lb). Motor: 1 x Castor 4A. Thrust (vac): 478.309 kN (107,528 lbf). Isp: 266 sec. Burn time: 56 sec. Length: 9.12 m (29.92 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor RS27. Gross Mass: 84,368 kg (185,999 lb). Empty Mass: 4,360 kg (9,610 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.218 kN (231,602 lbf). Isp: 296 sec. Burn time: 223 sec. Length: 22.37 m (73.39 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage0: 9 x Castor 4A. Gross Mass: 11,743 kg (25,888 lb). Empty Mass: 1,529 kg (3,370 lb). Motor: 1 x Castor 4A. Thrust (vac): 478.309 kN (107,528 lbf). Isp: 266 sec. Burn time: 56 sec. Length: 9.12 m (29.92 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor RS27. Gross Mass: 84,368 kg (185,999 lb). Empty Mass: 4,360 kg (9,610 lb). Motor: 1 x RS-27. Thrust (vac): 1,030.218 kN (231,602 lbf). Isp: 296 sec. Burn time: 223 sec. Length: 22.37 m (73.39 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

LEO Payload: 3,981 kg (8,776 lb). to: 185 km Orbit. Payload: 1,446 kg (3,187 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: DUVE, Eurostar 1000, EUVE, Geotail, GPS Block 2 and 2A, HS 376, LACE, RME, ROSAT. Liftoff Thrust: 3,480.600 kN (782,470 lbf). Total Mass: 218,000 kg (480,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 38.10 m (124.90 ft). Launch Price $: 36.700 million. in: 1987 price dollars. Version:

Delta 6920-8. Status: Retired 1990.

Three stage vehicle consisting of 9 x Castor 4A + 1 x EELT Thor/RS-27+ 1 x Delta K with 2.4 m (8 foot) diameter fairing)

Launches: 1. First Launch Date: 1990-02-14. Last Launch Date: 1990-02-14. Apogee: 1,000 km (600 mi). Liftoff Thrust: 3,790.000 kN (852,020 lbf). Total Mass: 219,000 kg (482,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 39.00 m (127.00 ft).

• Stage0: 9 x Castor 4A. Gross Mass: 11,743 kg (25,888 lb). Empty Mass: 1,529 kg (3,370 lb). Motor: 1 x Castor 4A. Thrust (vac): 478.309 kN (107,528 lbf). Isp: 266 sec. Burn time: 56 sec. Length: 9.12 m (29.92 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor XLT-C. Gross Mass: 101,900 kg (224,600 lb). Empty Mass: 5,900 kg (13,000 lb). Motor: 1 x RS-27C. Thrust (vac): 1,054.195 kN (236,992 lbf). Isp: 302 sec. Burn time: 265 sec. Length: 26.05 m (85.46 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage0: 9 x Castor 4A. Gross Mass: 11,743 kg (25,888 lb). Empty Mass: 1,529 kg (3,370 lb). Motor: 1 x Castor 4A. Thrust (vac): 478.309 kN (107,528 lbf). Isp: 266 sec. Burn time: 56 sec. Length: 9.12 m (29.92 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor XLT-C. Gross Mass: 101,900 kg (224,600 lb). Empty Mass: 5,900 kg (13,000 lb). Motor: 1 x RS-27C. Thrust (vac): 1,054.195 kN (236,992 lbf). Isp: 302 sec. Burn time: 265 sec. Length: 26.05 m (85.46 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage0: 9 x Castor 4A. Gross Mass: 11,743 kg (25,888 lb). Empty Mass: 1,529 kg (3,370 lb). Motor: 1 x Castor 4A. Thrust (vac): 478.309 kN (107,528 lbf). Isp: 266 sec. Burn time: 56 sec. Length: 9.12 m (29.92 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor XLT. Gross Mass: 101,700 kg (224,200 lb). Empty Mass: 5,690 kg (12,540 lb). Motor: 1 x RS-27A. Thrust (vac): 1,032.002 kN (232,003 lbf). Isp: 295 sec. Burn time: 274 sec. Length: 26.05 m (85.46 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage3: 1 x PAM-D. Gross Mass: 2,141 kg (4,720 lb). Empty Mass: 232 kg (511 lb). Motor: 1 x Star 48. Thrust (vac): 67.155 kN (15,097 lbf). Isp: 292 sec. Burn time: 88 sec. Length: 2.04 m (6.69 ft). Diameter: 1.24 m (4.06 ft). Propellants: Solid.

• Stage0: 9 x Castor 4A. Gross Mass: 11,743 kg (25,888 lb). Empty Mass: 1,529 kg (3,370 lb). Motor: 1 x Castor 4A. Thrust (vac): 478.309 kN (107,528 lbf). Isp: 266 sec. Burn time: 56 sec. Length: 9.12 m (29.92 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor XLT-C. Gross Mass: 101,900 kg (224,600 lb). Empty Mass: 5,900 kg (13,000 lb). Motor: 1 x RS-27C. Thrust (vac): 1,054.195 kN (236,992 lbf). Isp: 302 sec. Burn time: 265 sec. Length: 26.05 m (85.46 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage3: 1 x PAM-D. Gross Mass: 2,141 kg (4,720 lb). Empty Mass: 232 kg (511 lb). Motor: 1 x Star 48. Thrust (vac): 67.155 kN (15,097 lbf). Isp: 292 sec. Burn time: 88 sec. Length: 2.04 m (6.69 ft). Diameter: 1.24 m (4.06 ft). Propellants: Solid.

LEO Payload: 5,089 kg (11,219 lb). to: 185 km Orbit. Payload: 1,818 kg (4,008 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: ACE, Aqua, ARGOS, AS 3000, ASC, CHIPSat, Contour, Deep Space 1, ECS/OTS, EO-1, FUSE, GeoLITE, Globalstar, GPS Block 2 and 2A, GPS Block 2R, HS 376, HS 601, ICESat, IMAGE, Landsat 7, LM 700, Losat, MAP, Mars Climate Orbiter, Mars Global Surveyor. Other Associated Spacecraft: Mars Odyssey, Mars Pathfinder, Mars Polar Lander, MER, MSX, Munin, NEAR, Orsted, PMG, Polar, QuickBird, Radarsat, SAC-C, SEDS, SEDSAT, Spacebus 100, Stardust, Sunsat, SURFSAT-1, TIMED, Wind, XSS, XTE. Liftoff Thrust: 3,110.000 kN (699,150 lbf). Total Mass: 231,870 kg (511,180 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 38.10 m (124.90 ft). Launch Price $: 60.000 million. in: 1999 price dollars. Version:

Delta 7320-10. Status: Active.

Three stage vehicle consisting of 3 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K

Launches: 4. First Launch Date: 1999-06-24. Last Launch Date: 2003-01-13. Apogee: 1,000 km (600 mi). Liftoff Thrust: 2,500.000 kN (562,000 lbf). Total Mass: 151,700 kg (334,400 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 38.90 m (127.60 ft).

• Stage0: 3 x GEM 40. Gross Mass: 13,064 kg (28,801 lb). Empty Mass: 1,361 kg (3,000 lb). Motor: 1 x GEM 40. Thrust (vac): 492.931 kN (110,815 lbf). Isp: 274 sec. Burn time: 64 sec. Length: 12.96 m (42.51 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor XLT-C. Gross Mass: 101,900 kg (224,600 lb). Empty Mass: 5,900 kg (13,000 lb). Motor: 1 x RS-27C. Thrust (vac): 1,054.195 kN (236,992 lbf). Isp: 302 sec. Burn time: 265 sec. Length: 26.05 m (85.46 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage0: 3 x GEM 40. Gross Mass: 13,064 kg (28,801 lb). Empty Mass: 1,361 kg (3,000 lb). Motor: 1 x GEM 40. Thrust (vac): 492.931 kN (110,815 lbf). Isp: 274 sec. Burn time: 64 sec. Length: 12.96 m (42.51 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor XLT-C. Gross Mass: 101,900 kg (224,600 lb). Empty Mass: 5,900 kg (13,000 lb). Motor: 1 x RS-27C. Thrust (vac): 1,054.195 kN (236,992 lbf). Isp: 302 sec. Burn time: 265 sec. Length: 26.05 m (85.46 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage0: 3 x GEM 40. Gross Mass: 13,064 kg (28,801 lb). Empty Mass: 1,361 kg (3,000 lb). Motor: 1 x GEM 40. Thrust (vac): 492.931 kN (110,815 lbf). Isp: 274 sec. Burn time: 64 sec. Length: 12.96 m (42.51 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor XLT-C. Gross Mass: 101,900 kg (224,600 lb). Empty Mass: 5,900 kg (13,000 lb). Motor: 1 x RS-27C. Thrust (vac): 1,054.195 kN (236,992 lbf). Isp: 302 sec. Burn time: 265 sec. Length: 26.05 m (85.46 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage3: 1 x Star 37FM. Gross Mass: 1,147 kg (2,528 lb). Empty Mass: 81 kg (178 lb). Motor: 1 x Star 37FM. Thrust (vac): 47.900 kN (10,768 lbf). Burn time: 63 sec. Length: 1.70 m (5.50 ft). Diameter: 0.94 m (3.08 ft). Propellants: Solid.

Launches: 1. First Launch Date: 2007-12-09. Last Launch Date: 2007-12-09. Version:

Delta 7420-10C. Status: Active.

Three stage vehicle consisting of 4 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K with 3.05 m (10 foot) diameter composite fairing

Launches: 9. First Launch Date: 1998-02-14. Last Launch Date: 2007-06-08. Apogee: 1,500 km (900 mi). Liftoff Thrust: 3,020.000 kN (678,920 lbf). Total Mass: 165,000 kg (363,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 39.00 m (127.00 ft).

• Stage0: 4 x GEM 40. Gross Mass: 13,064 kg (28,801 lb). Empty Mass: 1,361 kg (3,000 lb). Motor: 1 x GEM 40. Thrust (vac): 492.931 kN (110,815 lbf). Isp: 274 sec. Burn time: 64 sec. Length: 12.96 m (42.51 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor XLT-C. Gross Mass: 101,900 kg (224,600 lb). Empty Mass: 5,900 kg (13,000 lb). Motor: 1 x RS-27C. Thrust (vac): 1,054.195 kN (236,992 lbf). Isp: 302 sec. Burn time: 265 sec. Length: 26.05 m (85.46 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage0: 4 x GEM 40. Gross Mass: 13,064 kg (28,801 lb). Empty Mass: 1,361 kg (3,000 lb). Motor: 1 x GEM 40. Thrust (vac): 492.931 kN (110,815 lbf). Isp: 274 sec. Burn time: 64 sec. Length: 12.96 m (42.51 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor XLT-C. Gross Mass: 101,900 kg (224,600 lb). Empty Mass: 5,900 kg (13,000 lb). Motor: 1 x RS-27C. Thrust (vac): 1,054.195 kN (236,992 lbf). Isp: 302 sec. Burn time: 265 sec. Length: 26.05 m (85.46 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage3: 1 x PAM-D. Gross Mass: 2,141 kg (4,720 lb). Empty Mass: 232 kg (511 lb). Motor: 1 x Star 48. Thrust (vac): 67.155 kN (15,097 lbf). Isp: 292 sec. Burn time: 88 sec. Length: 2.04 m (6.69 ft). Diameter: 1.24 m (4.06 ft). Propellants: Solid.

• Stage0: 4 x GEM 40. Gross Mass: 13,064 kg (28,801 lb). Empty Mass: 1,361 kg (3,000 lb). Motor: 1 x GEM 40. Thrust (vac): 492.931 kN (110,815 lbf). Isp: 274 sec. Burn time: 64 sec. Length: 12.96 m (42.51 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor XLT-C. Gross Mass: 101,900 kg (224,600 lb). Empty Mass: 5,900 kg (13,000 lb). Motor: 1 x RS-27C. Thrust (vac): 1,054.195 kN (236,992 lbf). Isp: 302 sec. Burn time: 265 sec. Length: 26.05 m (85.46 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage3: 1 x PAM-D. Gross Mass: 2,141 kg (4,720 lb). Empty Mass: 232 kg (511 lb). Motor: 1 x Star 48. Thrust (vac): 67.155 kN (15,097 lbf). Isp: 292 sec. Burn time: 88 sec. Length: 2.04 m (6.69 ft). Diameter: 1.24 m (4.06 ft). Propellants: Solid.

• Stage0: 4 x GEM 40. Gross Mass: 13,064 kg (28,801 lb). Empty Mass: 1,361 kg (3,000 lb). Motor: 1 x GEM 40. Thrust (vac): 492.931 kN (110,815 lbf). Isp: 274 sec. Burn time: 64 sec. Length: 12.96 m (42.51 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor XLT-C. Gross Mass: 101,900 kg (224,600 lb). Empty Mass: 5,900 kg (13,000 lb). Motor: 1 x RS-27C. Thrust (vac): 1,054.195 kN (236,992 lbf). Isp: 302 sec. Burn time: 265 sec. Length: 26.05 m (85.46 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage3: 1 x Star 37FM. Gross Mass: 1,147 kg (2,528 lb). Empty Mass: 81 kg (178 lb). Motor: 1 x Star 37FM. Thrust (vac): 47.900 kN (10,768 lbf). Burn time: 63 sec. Length: 1.70 m (5.50 ft). Diameter: 0.94 m (3.08 ft). Propellants: Solid.

• Stage0: 9 x GEM 40. Gross Mass: 13,064 kg (28,801 lb). Empty Mass: 1,361 kg (3,000 lb). Motor: 1 x GEM 40. Thrust (vac): 492.931 kN (110,815 lbf). Isp: 274 sec. Burn time: 64 sec. Length: 12.96 m (42.51 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor XLT-C. Gross Mass: 101,900 kg (224,600 lb). Empty Mass: 5,900 kg (13,000 lb). Motor: 1 x RS-27C. Thrust (vac): 1,054.195 kN (236,992 lbf). Isp: 302 sec. Burn time: 265 sec. Length: 26.05 m (85.46 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage0: 9 x GEM 40. Gross Mass: 13,064 kg (28,801 lb). Empty Mass: 1,361 kg (3,000 lb). Motor: 1 x GEM 40. Thrust (vac): 492.931 kN (110,815 lbf). Isp: 274 sec. Burn time: 64 sec. Length: 12.96 m (42.51 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor XLT-C. Gross Mass: 101,900 kg (224,600 lb). Empty Mass: 5,900 kg (13,000 lb). Motor: 1 x RS-27C. Thrust (vac): 1,054.195 kN (236,992 lbf). Isp: 302 sec. Burn time: 265 sec. Length: 26.05 m (85.46 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage0: 9 x GEM 40. Gross Mass: 13,064 kg (28,801 lb). Empty Mass: 1,361 kg (3,000 lb). Motor: 1 x GEM 40. Thrust (vac): 492.931 kN (110,815 lbf). Isp: 274 sec. Burn time: 64 sec. Length: 12.96 m (42.51 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor XLT-C. Gross Mass: 101,900 kg (224,600 lb). Empty Mass: 5,900 kg (13,000 lb). Motor: 1 x RS-27C. Thrust (vac): 1,054.195 kN (236,992 lbf). Isp: 302 sec. Burn time: 265 sec. Length: 26.05 m (85.46 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage0: 9 x GEM 40. Gross Mass: 13,064 kg (28,801 lb). Empty Mass: 1,361 kg (3,000 lb). Motor: 1 x GEM 40. Thrust (vac): 492.931 kN (110,815 lbf). Isp: 274 sec. Burn time: 64 sec. Length: 12.96 m (42.51 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor XLT-C. Gross Mass: 101,900 kg (224,600 lb). Empty Mass: 5,900 kg (13,000 lb). Motor: 1 x RS-27C. Thrust (vac): 1,054.195 kN (236,992 lbf). Isp: 302 sec. Burn time: 265 sec. Length: 26.05 m (85.46 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

Launches: 1. First Launch Date: 2003-08-25. Last Launch Date: 2003-08-25. LEO Payload: 1,816 kg (4,003 lb). Payload: 1,000 kg (2,200 lb). to a: earth escape trajectory. Associated Spacecraft: MER, SIRTF. Liftoff Thrust: 4,510.000 kN (1,013,880 lbf). Total Mass: 286,000 kg (630,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 39.00 m (127.00 ft).

• Stage0: 9 x GEM 46. Gross Mass: 19,327 kg (42,608 lb). Empty Mass: 2,282 kg (5,030 lb). Motor: 1 x GEM 46. Thrust (vac): 628.310 kN (141,250 lbf). Isp: 278 sec. Burn time: 75 sec. Length: 14.70 m (48.20 ft). Diameter: 1.17 m (3.83 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor XLT-C. Gross Mass: 101,900 kg (224,600 lb). Empty Mass: 5,900 kg (13,000 lb). Motor: 1 x RS-27C. Thrust (vac): 1,054.195 kN (236,992 lbf). Isp: 302 sec. Burn time: 265 sec. Length: 26.05 m (85.46 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage3: 1 x PAM-D. Gross Mass: 2,141 kg (4,720 lb). Empty Mass: 232 kg (511 lb). Motor: 1 x Star 48. Thrust (vac): 67.155 kN (15,097 lbf). Isp: 292 sec. Burn time: 88 sec. Length: 2.04 m (6.69 ft). Diameter: 1.24 m (4.06 ft). Propellants: Solid.

• Stage0: 9 x GEM 40. Gross Mass: 13,064 kg (28,801 lb). Empty Mass: 1,361 kg (3,000 lb). Motor: 1 x GEM 40. Thrust (vac): 492.931 kN (110,815 lbf). Isp: 274 sec. Burn time: 64 sec. Length: 12.96 m (42.51 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor XLT-C. Gross Mass: 101,900 kg (224,600 lb). Empty Mass: 5,900 kg (13,000 lb). Motor: 1 x RS-27C. Thrust (vac): 1,054.195 kN (236,992 lbf). Isp: 302 sec. Burn time: 265 sec. Length: 26.05 m (85.46 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage3: 1 x PAM-D. Gross Mass: 2,141 kg (4,720 lb). Empty Mass: 232 kg (511 lb). Motor: 1 x Star 48. Thrust (vac): 67.155 kN (15,097 lbf). Isp: 292 sec. Burn time: 88 sec. Length: 2.04 m (6.69 ft). Diameter: 1.24 m (4.06 ft). Propellants: Solid.

• Stage0: 9 x GEM 40. Gross Mass: 13,064 kg (28,801 lb). Empty Mass: 1,361 kg (3,000 lb). Motor: 1 x GEM 40. Thrust (vac): 492.931 kN (110,815 lbf). Isp: 274 sec. Burn time: 64 sec. Length: 12.96 m (42.51 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor XLT-C. Gross Mass: 101,900 kg (224,600 lb). Empty Mass: 5,900 kg (13,000 lb). Motor: 1 x RS-27C. Thrust (vac): 1,054.195 kN (236,992 lbf). Isp: 302 sec. Burn time: 265 sec. Length: 26.05 m (85.46 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage3: 1 x PAM-D. Gross Mass: 2,141 kg (4,720 lb). Empty Mass: 232 kg (511 lb). Motor: 1 x Star 48. Thrust (vac): 67.155 kN (15,097 lbf). Isp: 292 sec. Burn time: 88 sec. Length: 2.04 m (6.69 ft). Diameter: 1.24 m (4.06 ft). Propellants: Solid.

• Stage0: 9 x GEM 40. Gross Mass: 13,064 kg (28,801 lb). Empty Mass: 1,361 kg (3,000 lb). Motor: 1 x GEM 40. Thrust (vac): 492.931 kN (110,815 lbf). Isp: 274 sec. Burn time: 64 sec. Length: 12.96 m (42.51 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor XLT-C. Gross Mass: 101,900 kg (224,600 lb). Empty Mass: 5,900 kg (13,000 lb). Motor: 1 x RS-27C. Thrust (vac): 1,054.195 kN (236,992 lbf). Isp: 302 sec. Burn time: 265 sec. Length: 26.05 m (85.46 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage3: 1 x PAM-D. Gross Mass: 2,141 kg (4,720 lb). Empty Mass: 232 kg (511 lb). Motor: 1 x Star 48. Thrust (vac): 67.155 kN (15,097 lbf). Isp: 292 sec. Burn time: 88 sec. Length: 2.04 m (6.69 ft). Diameter: 1.24 m (4.06 ft). Propellants: Solid.

• Stage0: 9 x GEM 40. Gross Mass: 13,064 kg (28,801 lb). Empty Mass: 1,361 kg (3,000 lb). Motor: 1 x GEM 40. Thrust (vac): 492.931 kN (110,815 lbf). Isp: 274 sec. Burn time: 64 sec. Length: 12.96 m (42.51 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor XLT-C. Gross Mass: 101,900 kg (224,600 lb). Empty Mass: 5,900 kg (13,000 lb). Motor: 1 x RS-27C. Thrust (vac): 1,054.195 kN (236,992 lbf). Isp: 302 sec. Burn time: 265 sec. Length: 26.05 m (85.46 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage3: 1 x PAM-D. Gross Mass: 2,141 kg (4,720 lb). Empty Mass: 232 kg (511 lb). Motor: 1 x Star 48. Thrust (vac): 67.155 kN (15,097 lbf). Isp: 292 sec. Burn time: 88 sec. Length: 2.04 m (6.69 ft). Diameter: 1.24 m (4.06 ft). Propellants: Solid.

• Stage0: 9 x GEM 40. Gross Mass: 13,064 kg (28,801 lb). Empty Mass: 1,361 kg (3,000 lb). Motor: 1 x GEM 40. Thrust (vac): 492.931 kN (110,815 lbf). Isp: 274 sec. Burn time: 64 sec. Length: 12.96 m (42.51 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor XLT-C. Gross Mass: 101,900 kg (224,600 lb). Empty Mass: 5,900 kg (13,000 lb). Motor: 1 x RS-27C. Thrust (vac): 1,054.195 kN (236,992 lbf). Isp: 302 sec. Burn time: 265 sec. Length: 26.05 m (85.46 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage3: 1 x PAM-D. Gross Mass: 2,141 kg (4,720 lb). Empty Mass: 232 kg (511 lb). Motor: 1 x Star 48. Thrust (vac): 67.155 kN (15,097 lbf). Isp: 292 sec. Burn time: 88 sec. Length: 2.04 m (6.69 ft). Diameter: 1.24 m (4.06 ft). Propellants: Solid.

• Stage4: 1 x PAM-D2. Gross Mass: 3,697 kg (8,150 lb). Empty Mass: 431 kg (950 lb). Motor: 1 x Star 63. Thrust (vac): 107.196 kN (24,099 lbf). Isp: 282 sec. Burn time: 120 sec. Length: 1.83 m (6.00 ft). Diameter: 1.60 m (5.20 ft). Propellants: Solid.

• Stage0: 9 x GEM 46. Gross Mass: 19,327 kg (42,608 lb). Empty Mass: 2,282 kg (5,030 lb). Motor: 1 x GEM 46. Thrust (vac): 628.310 kN (141,250 lbf). Isp: 278 sec. Burn time: 75 sec. Length: 14.70 m (48.20 ft). Diameter: 1.17 m (3.83 ft). Propellants: Solid.

• Stage1: 1 x Delta Thor XLT-C. Gross Mass: 101,900 kg (224,600 lb). Empty Mass: 5,900 kg (13,000 lb). Motor: 1 x RS-27C. Thrust (vac): 1,054.195 kN (236,992 lbf). Isp: 302 sec. Burn time: 265 sec. Length: 26.05 m (85.46 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Motor: 1 x AJ10-118K. Thrust (vac): 43.630 kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Length: 5.89 m (19.32 ft). Diameter: 1.70 m (5.50 ft). Propellants: N2O4/Aerozine-50.

• Stage3: 1 x PAM-D. Gross Mass: 2,141 kg (4,720 lb). Empty Mass: 232 kg (511 lb). Motor: 1 x Star 48. Thrust (vac): 67.155 kN (15,097 lbf). Isp: 292 sec. Burn time: 88 sec. Length: 2.04 m (6.69 ft). Diameter: 1.24 m (4.06 ft). Propellants: Solid.

Launches: 3. Failures: 2. First Launch Date: 1998-08-27. Last Launch Date: 2000-08-23. LEO Payload: 8,292 kg (18,280 lb). to: 185 km Orbit. at: 28.70 degrees. Payload: 3,810 kg (8,390 lb). to a: Geosynchronous transfer trajectory. Apogee: 40,000 km (24,000 mi). Associated Spacecraft: HS 601. Liftoff Thrust: 4,889.500 kN (1,099,203 lbf). Total Mass: 301,450 kg (664,580 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 35.00 m (114.00 ft). Launch Price $: 90.000 million. in: 1999 price dollars.

• Stage0: 9 x GEM 46. Gross Mass: 19,327 kg (42,608 lb). Empty Mass: 2,282 kg (5,030 lb). Motor: 1 x GEM 46. Thrust (vac): 628.310 kN (141,250 lbf). Isp: 278 sec. Burn time: 75 sec. Length: 14.70 m (48.20 ft). Diameter: 1.17 m (3.83 ft). Propellants: Solid.

• Stage1: 1 x Delta 3 - 1. Gross Mass: 104,377 kg (230,111 lb). Empty Mass: 6,822 kg (15,039 lb). Motor: 1 x RS-27A. Thrust (vac): 1,085.790 kN (244,095 lbf). Isp: 302 sec. Burn time: 320 sec. Length: 20.00 m (65.00 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Delta 3-2. Gross Mass: 19,300 kg (42,500 lb). Empty Mass: 2,476 kg (5,458 lb). Motor: 1 x RL-10B-2. Thrust (vac): 110.030 kN (24,736 lbf). Isp: 462 sec. Burn time: 700 sec. Length: 8.80 m (28.80 ft). Diameter: 2.44 m (8.00 ft). Propellants: Lox/LH2.

1955 December 1 - Missile programs get highest priority. President Eisenhower assigned highest priority to ICBM and Thor and Jupiter IRBM programs.

1956 August 27 - Thor engine first static test. First static firing of Thor rocket engine at AFFTC, Edwards AFB.

1957 January 26 - Cape Canaveral LC17B. Thor DM-18 101 FAILURE: Lox contamination, led to a valve failure. Thrust decayed, the booster settled back through the thrust ring, causing an oxygen fire, followed by booster explosion. Series I research and development launch Agency: USAF 6555 ATW. Apogee: 0 km ( mi). First attempted test flight of USAF Thor IRBM, only 13 months after first production contracts were signed, failed to launch.

1957 April 20 - 04:33 GMT - Cape Canaveral LC17B. Thor DM-18 102 FAILURE: Console wiring error resulted in erroneous tracking indication; destroyed by range safety. Series I research and development launch Agency: USAF 6555 ATW. Apogee: 0 km ( mi). Douglas Thor IRBM (XSM-75) was launched at Cape Canaveral, Fla., destroyed by range safety officer. The missile was actually on course throughout its flight. The console wiring error led the range safety officer to believe it was headed inland rather than out to sea, so he hit the destruct button.

1957 May 22 - 03:00 GMT - Cape Canaveral LC17B. Thor DM-18 103 Research and development Series I (padex) test Agency: USAF 6555 ATW. Apogee: 0 km ( mi).

1957 August 30 - Cape Canaveral LC17A. Thor DM-18 104 FAILURE: Failure. Series I research and development launch Agency: USAF 6555 ATW. Apogee: 0 km ( mi).

1957 September 20 - Cape Canaveral LC17B. Thor DM-18 105 Series I research and development launch Agency: USAF 6555 ATW. Apogee: 520 km (320 mi). Complete USAF Thor IRBM first successfully launched from Cape Canaveral. Dummy Warhead sent to 1800 km range.

1957 October 3 - 17:13 GMT - Cape Canaveral LC17A. Thor DM-18 107 FAILURE: Failure. Series I research and development launch Agency: USAF 6555 ATW. Apogee: 0 km ( mi).

1957 October 11 - 16:33 GMT - Cape Canaveral LC17B. Thor DM-18 108 FAILURE: Turbopump gearbox failure. Series I research and development launch Agency: USAF 6555 ATW. Apogee: 520 km (320 mi). Thor missile launched at Cape Canaveral, the second tested, achieved its designed 1,500-mile range.

1957 October 24 - 16:32 GMT - Cape Canaveral LC17A. Thor DM-18 109 Series I research and development launch Agency: USAF 6555 ATW. Apogee: 520 km (320 mi). Stripped down Thor long-range flight test successful from AMR, impacting 4400 km downrange.

1957 November 27 - Thor and Jupiter IRBM's ordered into production. Thor and Jupiter IRBM's ordered into production for ultimate deployment by the USAF.

1957 December 7 - 22:11 GMT - Cape Canaveral LC17B. Thor DM-18 112 Research and development Series II test Agency: USAF 6555 ATW. Apogee: 520 km (320 mi).

1957 December 19 - 20:12 GMT - Cape Canaveral LC17A. Thor DM-18 113 Research and development Series II test Agency: USAF 6555 ATW. Apogee: 520 km (320 mi). A Thor missile, the eighth tested and the fourth successfully, completed the first fully-guided Thor IRBM flight using an all-inertial guidance system.

1958 January 1 - Thor put into operational service. Strategic Air Command assigned responsibility for U.S. operational ICBM capability; while the 672nd Strategic Missile Squadron, first to be equipped with USAF Douglas Thor IRBM, was activated.

1958 January 28 - 20:16 GMT - Cape Canaveral LC17A. Thor DM-18 114 FAILURE: Failure. Research and development Series II test Agency: USAF 6555 ATW. Apogee: 0 km ( mi). Thor IRBM successfully fired from Cape Canaveral, flew prescribed course, and impacted in preselected area.

1958 February 28 - 13:08 GMT - Cape Canaveral LC17B. Thor DM-18 120 FAILURE: Failure. Research and development Series II test Agency: USAF 6555 ATW. Apogee: 0 km ( mi). Copper heatsink nose cone

1958 April 19 - 13:30 GMT - Cape Canaveral LC17B. Thor DM-18 121 FAILURE: Failure. Research and development Series II test Agency: USAF 6555 ATW. Apogee: 0 km ( mi).

1958 April 24 - 00:10 GMT - Cape Canaveral LC17A. Thor Able 116 FAILURE: Thor turbopump gearbox failed T+150 sec. Able RTV re-entry vehicle test flight Agency: USAF 6555ATW. Apogee: 0 km ( mi). Mouse 'Mia' not recovered.

1958 June 4 - 21:17 GMT - Cape Canaveral LC18B. Thor DM-18 115 Research and development Series III test Agency: USAF 6555 ATW. Apogee: 520 km (320 mi). USAF Thor flight tested for the first time from a tactical-type launcher at Cape Canaveral.

1958 June 13 - 15:06 GMT - Cape Canaveral LC17B. Thor DM-18 122 Research and development Series III test Agency: USAF 6555 ATW. Apogee: 520 km (320 mi).

1958 July 10 - 02:30 GMT - Cape Canaveral LC17A. Thor Able 118 Able RTV re-entry vehicle test flight Agency: USAF 6555ATW. Apogee: 1,600 km (900 mi). Mouse 'Mia II' reached 1600 km altitude, flew 9600 km range, but re-entry vehicle not recovered.

1958 July 13 - 06:36 GMT - Cape Canaveral LC17B. Thor DM-18 123 Research and development Series III test Agency: USAF 6555 ATW. Apogee: 520 km (320 mi).

1958 July 23 - 22:13 GMT - Cape Canaveral LC17A. Thor Able 119 Able RTV re-entry vehicle test flight Agency: USAF 6555ATW. Apogee: 1,600 km (900 mi). Mouse 'Wickie' not recovered; nose cone lost.

1958 July 26 - 06:40 GMT - Cape Canaveral LC17B. Thor DM-18 126 FAILURE: Failure. Research and development Series III test Agency: USAF 6555 ATW. Apogee: 0 km ( mi).

1958 August 6 - Cape Canaveral LC18B. Thor DM-18 117 Research and development Series III test Agency: USAF. Apogee: 520 km (320 mi).

1958 August 17 - 12:18 GMT - Cape Canaveral LC17A. Thor Able I 127 FAILURE: Thor exploded after 77 sec. Pioneer (1) Mass: 38 kg (83 lb). Spacecraft: Pioneer 0-1-2. Agency: U.S. Air Force. Apogee: 16 km (9 mi). First US lunar attempt. The first US Air Force lunar probe, using a Thor-Able booster. An explosion ripped it apart 77 seconds after launch.

1958 October 11 - 08:42 GMT - Cape Canaveral LC17A. Thor Able I 130 FAILURE: Third stage produced insufficient thrust. Partial Failure. Pioneer 1 Mass: 38 kg (83 lb). Spacecraft: Pioneer 0-1-2. Agency: NASA. Set distance record; failed to reach moon.

1958 November 5 - 08:53 GMT - Cape Canaveral LC17B. Thor DM-18A 138 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1958 November 8 - 07:30 GMT - Cape Canaveral LC17A. Thor Able I 129 FAILURE: Third stage ignition unsuccessful. Pioneer 2 Mass: 39 kg (85 lb). Spacecraft: Pioneer 0-1-2. Agency: NASA. Apogee: 1,550 km (960 mi). Pioneer 2 was launched from the Atlantic Missile Range, using a Thor-Able booster, the Air Force acting as executive agent to NASA. The 86.3-pound instrumented payload, intended as a lunar probe, failed to reach escape velocity.

1958 November 26 - 09:09 GMT - Cape Canaveral LC17B. Thor DM-18A 140 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi). First operational launch

1958 December 6 - 00:41 GMT - Cape Canaveral LC18B. Thor DM-18A 145 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1958 December 16 - 23:44 GMT - Vandenberg SLC2E. Thor DM-18A 151 Operational missile test Agency: USAF. Apogee: 520 km (320 mi). Two Thor shots, one from Cape Canaveral and one from Vandenberg AFB, were successful. Intermediate range ballistic missile portion of PMR was inaugurated with successful firing of USAF Thor from Vandenberg AFB.

1958 December 17 - 04:00 GMT - Cape Canaveral LC17B. Thor DM-18A 146 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1958 December 31 - 02:00 GMT - Cape Canaveral LC18B. Thor DM-18A 149 FAILURE: Failure. Series IV research and development launch Agency: USAF.

1959 January 21 - Vandenberg SLC1W. Thor Agena A 160 FAILURE: Launch vehicle failure. Thor Agena test Spacecraft: KH-1. Agency: USAF. First flight test of Thor-Agena for KH program.

1959 January 23 - Cape Canaveral LC17A. Thor Able II 128 FAILURE: Failure. RVX-1 Re-entry Vehicle test Agency: USAF. Apogee: 0 km ( mi).

1959 January 30 - 23:53 GMT - Cape Canaveral LC17B. Thor DM-18A 154 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1959 February 28 - 07:58 GMT - Cape Canaveral LC17A. Thor Able II 131 RVX-1 Re-entry Vehicle test Agency: USAF. Apogee: 520 km (320 mi).

1959 February 28 - 21:49 GMT - Vandenberg SLC1W. Thor Agena A 163 / Agena A 1022 Discoverer 1 Mass: 618 kg (1,362 lb). Spacecraft: KH-1. Agency: DARPA. Perigee: 163 km (101 mi). Apogee: 968 km (601 mi). Inclination: 89.70 deg. Period: 96.00 min. First polar orbiting satellite; KH-1 prototype; did not carry camera or film capsule.

1959 March 21 - 06:19 GMT - Cape Canaveral LC17A. Thor Able II 132 RVX-1 Re-entry Vehicle test Agency: USAF. Apogee: 520 km (320 mi).

1959 March 22 - 00:58 GMT - Cape Canaveral LC18B. Thor DM-18A 158 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1959 March 27 - 04:02 GMT - Cape Canaveral LC17B. Thor DM-18A 162 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1959 April 8 - 06:35 GMT - Cape Canaveral LC17A. Thor Able II 133 RVX-1 Reentry test / particles mission Agency: USAF. Apogee: 1,230 km (760 mi).

1959 April 13 - 21:18 GMT - Vandenberg SLC1W. Thor Agena A 170 / Agena A 1018 Discoverer 2 Mass: 743 kg (1,638 lb). Spacecraft: KH-1. Agency: DARPA. Perigee: 239 km (148 mi). Apogee: 346 km (214 mi). Inclination: 89.90 deg. Period: 90.40 min. KH-1 prototype; tested capsule recovery techniques; did not carry camera; capsule recovery failed. Because of a timing error, the US believed that the capsule landed somewhere on the island of Spitsbergen, north of Norway, instead of landing in the recovery zone near Hawaii. The capsule was never found; and CIA officials suspect it may have been snatched by the Soviets. The search for this capsule formed the basis of the book and film 'Ice Station Zebra'.

In the winter of 1960/1961, a US Discovery spy satellite capsule was found by loggers near Kalinin, 200 km north of Moscow. The loggers cracked it open with an axe. Sergei Khrushchev believed this to be the Discoverer 2 capsule. What was left was examined by Soviet engineers but didn’t reveal much information - it was a polished aluminium sphere, 30 cm in diameter, gilded on the exterior. Some said it was found as early as the winter of 1959.

1959 April 16 - 20:46 GMT - Vandenberg LE-8. Thor DM-18A 161 IWST test flight Agency: RAF. Apogee: 520 km (320 mi). Integrated Weapon System Training 1. First Thor IRBM launched by British crew at Vandenberg AFB.

1959 April 23 - 05:30 GMT - Cape Canaveral LC17B. Thor DM-18A 176 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi). Fourth recovery of a data capsule at AMR, USAF Thor 1,500-mile accuracy test flight.

1959 April 25 - 05:00 GMT - Cape Canaveral LC18B. Thor DM-18A 164 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1959 April 28 - Delta launch vehicle contract. NASA announced the signing of a $24 million contract with Douglas Aircraft Co., Inc., for a three-stage Thor-Vanguard launching rocket called Delta.

1959 May 12 - 17:35 GMT - Cape Canaveral LC17B. Thor DM-18A 187 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1959 May 21 - 06:40 GMT - Cape Canaveral LC17A. Thor Able II 135 RVX-1 Re-entry Vehicle test Agency: USAF. Apogee: 520 km (320 mi).

1959 May 23 - 02:42 GMT - Cape Canaveral LC18B. Thor DM-18A 184 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1959 June 3 - 20:09 GMT - Vandenberg SLC1W. Thor Agena A 174 / Agena A 1020 FAILURE: No telemetry after Agena ignition. Discoverer 3 Mass: 753 kg (1,660 lb). Spacecraft: KH-1. Agency: DARPA. KH-1 prototype; did not carry camera; film capsule recovery failed.

1959 June 11 - 06:44 GMT - Cape Canaveral LC17A. Thor Able II 137 RVX-1 Re-entry Vehicle test Agency: USAF. Apogee: 520 km (320 mi).

1959 June 16 - 21:45 GMT - Vandenberg SLC10E. Thor DM-18A 191 FAILURE: Autopilot error. IWST test flight Agency: RAF. Apogee: 0 km ( mi). Integrated Weapon System Training Launch 2

1959 June 25 - 22:47 GMT - Vandenberg SLC1E. Thor Agena A 179 / Agena A 1023 FAILURE: Insufficient stage 2 velocity. Discoverer 4 Mass: 743 kg (1,638 lb). Spacecraft: KH-1. Agency: DARPA. KH-1; 1st generation low resolution photo surveillance. Failed to achieve orbit.

1959 June 26 - Cape Canaveral LC18B. Thor DM-18A 198 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1959 June 30 - 02:37 GMT - Cape Canaveral LC17B. Thor DM-18A 194 Series IV Lofted Trajectory research and development mission Agency: USAF. Apogee: 1,000 km (600 mi).

1959 July 21 - 07:33 GMT - Cape Canaveral LC17B. Thor DM-18A 203 FAILURE: Failure. Series IV research and development launch Agency: USAF. Apogee: 1.00 km (0.60 mi).

1959 July 24 - 12:47 GMT - Cape Canaveral LC18B. Thor DM-18A 202 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi). USAF Thor data capsule recovered near Antigua which contained movie film showing nose cone separation.

1959 August 3 - 21:41 GMT - Vandenberg SLC2E. Thor DM-18A 175 IWST Agency: RAF. Apogee: 520 km (320 mi).

1959 August 6 - 02:48 GMT - Cape Canaveral LC17B. Thor DM-18A 208 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1959 August 7 - 14:24 GMT - Cape Canaveral LC17A. Thor Able III 134 Explorer 6 Mass: 64 kg (141 lb). Spacecraft: S-2. Agency: NASA. Perigee: 245 km (152 mi). Apogee: 42,400 km (26,300 mi). Inclination: 47.00 deg. Period: 765.00 min. First Earth photo; radiation data.

1959 August 13 - 19:00 GMT - Vandenberg SLC1W. Thor Agena A 192 / Agena A 1029 Discoverer 5 Mass: 781 kg (1,721 lb). Spacecraft: KH-1. Agency: DARPA. Perigee: 214 km (132 mi). Apogee: 731 km (454 mi). Inclination: 79.90 deg. Period: 94.10 min. KH-1; 1st generation low resolution photo surveillance; film capsule boosted into higher orbit, decayed 2/11/61. Mission failed. Power supply failure. No recovery.

1959 August 14 - 09:00 GMT - Cape Canaveral LC18B. Thor DM-18A 204 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1959 August 14 - 19:36 GMT - Vandenberg SLC10W. Thor DM-18A 190 FAILURE: Failure. IWST Agency: RAF. Apogee: 0 km ( mi).

1959 August 19 - 19:24 GMT - Vandenberg SLC1E. Thor Agena A 200 / Agena A 1028 Discoverer 6 Mass: 783 kg (1,726 lb). Spacecraft: KH-1. Agency: DARPA. Perigee: 207 km (128 mi). Apogee: 846 km (525 mi). Inclination: 83.90 deg. Period: 95.10 min. KH-1; 1st generation low resolution photo surveillance; film capsule recovery failed. Mission failed. Retro rockets malfunctioned negating recovery.

1959 August 27 - 12:30 GMT - Cape Canaveral LC17B. Thor DM-18A 216 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1959 September 12 - Cape Canaveral LC18B. Thor DM-18A 217 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1959 September 17 - Cape Canaveral LC17A. Thor Able II-M1 136 FAILURE: Third stage failed. Transit 1A Mass: 119 kg (262 lb). Spacecraft: Transit. Agency: DARPA. First Transit test satellite; failed to reach orbit.

1959 September 17 - 21:09 GMT - Vandenberg SLC2W. Thor DM-18A 228 IWST Agency: RAF. Apogee: 520 km (320 mi).

1959 September 22 - 18:00 GMT - Cape Canaveral LC17B. Thor DM-18A 222 Series IV research and development launch/Ionosphere/Meteorites mission Agency: USAF. Apogee: 520 km (320 mi).

1959 October 6 - 16:41 GMT - Cape Canaveral LC18B. Thor DM-18A 235 Series IV research and development launch/Meteorites mission Agency: USAF. Apogee: 520 km (320 mi).

1959 October 6 - 18:26 GMT - Vandenberg LE-8. Thor DM-18A 239 IWST Agency: RAF. Apogee: 520 km (320 mi).

1959 October 14 - 04:15 GMT - Cape Canaveral LC17B. Thor DM-18A 221 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1959 October 21 - 22:57 GMT - Vandenberg SLC2E. Thor DM-18A 220 IWST Agency: RAF. Apogee: 520 km (320 mi).

1959 October 29 - 02:12 GMT - Cape Canaveral LC18B. Thor DM-18A 230 Series IV research and development launch/Meteorites mission Agency: USAF. Apogee: 520 km (320 mi).

1959 November 3 - Cape Canaveral LC17B. Thor DM-18A 238 Series IV research and development launch/Meteorites mission Agency: USAF. Apogee: 520 km (320 mi).

1959 November 7 - 20:28 GMT - Vandenberg SLC1W. Thor Agena A 206 / Agena A 1051 Discoverer 7 Mass: 794 kg (1,750 lb). Spacecraft: KH-1. Agency: DARPA. Perigee: 158 km (98 mi). Apogee: 820 km (500 mi). Inclination: 81.60 deg. Period: 94.40 min. KH-1; 1st generation low resolution photo surveillance; satellite tumbled; film capsule not recovered. Mission failed. Failed to achieve orbit.

1959 November 12 - 19:24 GMT - Vandenberg SLC2W. Thor DM-18A 181 IWST Agency: RAF. Apogee: 520 km (320 mi).

1959 November 19 - Cape Canaveral LC17B. Thor DM-18A 244 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1959 November 20 - 19:25 GMT - Vandenberg SLC1E. Thor Agena A 212 / Agena A 1050 Discoverer 8 Mass: 795 kg (1,752 lb). Spacecraft: KH-1. Agency: U.S. Air Force. Perigee: 186 km (115 mi). Apogee: 1,661 km (1,032 mi). Inclination: 80.50 deg. Period: 103.50 min. KH-1; 1st generation low resolution photo surveillance; film capsule recovery failed. Mission failed. Eccentric orbit negating recovery.

1959 December 1 - 17:00 GMT - Cape Canaveral LC18B. Thor DM-18A 254 Series IV research and development launch Agency: USAF. Apogee: 520 km (320 mi).

1959 December 2 - 05:29 GMT - Vandenberg SLC2E. Thor DM-18A 265 FAILURE: Failure. Combat training launch Agency: RAF. Apogee: 0 km ( mi).

1959 December 15 - 02:14 GMT - Vandenberg SLC2W. Thor DM-18A 185 FAILURE: Failure. IWST Agency: RAF. Apogee: 0 km ( mi).

1959 December 17 - Cape Canaveral LC17B. Thor DM-18A 255 Series IV research and development launch/Meteorites mission Agency: USAF. Apogee: 520 km (320 mi).

1960 January 14 - 16:35 GMT - Cape Canaveral LC18B. Thor DM-18C 256 Special test Agency: USAF. Apogee: 520 km (320 mi).

1960 January 21 - 20:10 GMT - Vandenberg SLC2W. Thor DM-18A 215 IWST Agency: RAF. Apogee: 520 km (320 mi).

1960 February 4 - 18:51 GMT - Vandenberg SLC1W. Thor Agena A 218 / Agena A 1052 FAILURE: Failure. Discoverer 9 Mass: 765 kg (1,686 lb). Spacecraft: KH-1. Agency: U.S. Air Force. KH-1; 1st generation low resolution photo surveillance. Mission failed.

1960 February 9 - 17:11 GMT - Cape Canaveral LC18B. Thor DM-18C 259 Special test Agency: USAF. Apogee: 520 km (320 mi).

1960 February 19 - 20:15 GMT - Vandenberg SLC1E. Thor Agena A 223 / Agena A 1054 FAILURE: Failure. Discoverer 10 Mass: 765 kg (1,686 lb). Spacecraft: KH-1. Agency: U.S. Air Force. KH-1; Mission failed.

1960 February 29 - Cape Canaveral LC18B. Thor DM-18C 263 Special test Agency: USAF. Apogee: 520 km (320 mi).

1960 March 2 - 20:06 GMT - Vandenberg LE-8. Thor DM-18A 272 Combat training launch Agency: RAF. Apogee: 520 km (320 mi).

1960 March 11 - 13:00 GMT - Cape Canaveral LC17A. Thor Able IV 219 Pioneer 5 Mass: 43 kg (94 lb). Spacecraft: Pioneer 5. Agency: NASA. Solar research. Solar Orbit (Heliocentric). Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1960 April 1 - 11:40 GMT - Cape Canaveral LC17A. Thor Able II-M1 148 Tiros 1 Mass: 120 kg (260 lb). Spacecraft: Tiros. Agency: NASA. Perigee: 656 km (407 mi). Apogee: 696 km (432 mi). Inclination: 48.40 deg. Period: 98.30 min. TV and Infrared Observation Satellite; returned 22952 cloud cover photos. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1960 April 13 - 12:02 GMT - Cape Canaveral LC17B. Thor Ablestar 257 AB002? Transit 1B Mass: 121 kg (266 lb). Spacecraft: Transit. Agency: DARPA. Perigee: 363 km (225 mi). Apogee: 644 km (400 mi). Inclination: 51.20 deg. Period: 94.60 min. The Able-Star second stage demonstrated the first engine restart in space and the feasibility of using satellites as navigational aids. The first experimental Transit satellite to achieve orbit operated for 89 days. It transmitted on two frequency pairs to test the technique for refraction correction and to determine if the transmitted frequencies should be close together or far apart. It also tested a magnetic torque device for spacecraft attitude control - the first satellite to do so.

1960 April 15 - 20:30 GMT - Vandenberg SLC1E. Thor Agena A 234 / Agena A 1055 Discoverer 11 Mass: 790 kg (1,740 lb). Spacecraft: KH-1. Agency: U.S. Air Force. Perigee: 166 km (103 mi). Apogee: 603 km (374 mi). Inclination: 80.40 deg. Period: 92.20 min. KH-1; film capsule recovery failed. Mission failed. Attitude control system malfunctioned.

1960 May 13 - 09:16 GMT - Cape Canaveral LC17A. Thor Delta 144/D1 FAILURE: Second stage attitude control failure. Echo 1 Mass: 56 kg (123 lb). Spacecraft: Echo. Agency: NASA.

1960 June 22 - 05:54 GMT - Cape Canaveral LC17B. Thor Ablestar 281 AB003? Transit 2A Mass: 101 kg (222 lb). Spacecraft: Transit. Agency: U.S. Navy. Perigee: 604 km (375 mi). Apogee: 988 km (613 mi). Inclination: 66.70 deg. Period: 100.80 min. Also returned geodetic data. Similar to Transit 1B, it transmitted until 26 October 1962. A planned Transit 2B was considered redundant and never built.

1960 June 22 - 23:26 GMT - Vandenberg SLC10E. Thor DM-18A 233 Combat training launch Agency: RAF. Apogee: 520 km (320 mi).

1960 June 29 - 22:00 GMT - Vandenberg SLC1W. Thor Agena A 160 / Agena A 1053 FAILURE: Failure. Discoverer 12 Mass: 790 kg (1,740 lb). Spacecraft: KH-1. Agency: U.S. Air Force. KH-1 prototype; designed to test capsule recovery system; did not carry camera.

1960 August 10 - 20:37 GMT - Vandenberg SLC1E. Thor Agena A 231 / Agena A 1057 Discoverer 13 Mass: 850 kg (1,870 lb). Spacecraft: KH-1. Agency: U.S. Air Force. Perigee: 258 km (160 mi). Apogee: 683 km (424 mi). Inclination: 82.80 deg. Period: 94.00 min. KH-1 prototype; designed to test capsule recovery system; did not carry camera; capsule successfully recovered from ocean.

1960 August 12 - 09:39 GMT - Cape Canaveral LC17A. Thor Delta 270/D2 Echo 1 Mass: 76 kg (167 lb). Spacecraft: Echo. Agency: NASA. Perigee: 966 km (600 mi). Apogee: 2,157 km (1,340 mi). Inclination: 47.30 deg. Period: 117.30 min. Balloon; passively relayed TV and voice transmissions. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1960 August 18 - 19:57 GMT - Vandenberg SLC1W. Thor Agena A 237 / Agena A 1056 Discoverer 14 Mass: 850 kg (1,870 lb). Spacecraft: KH-1. Agency: U.S. Air Force. Perigee: 177 km (109 mi). Apogee: 803 km (498 mi). Inclination: 79.60 deg. Period: 94.40 min. KH-1; film capsule recovered 1.2 days later; 1st successful photosurveillance mission. First successful mission. Cameras operated satisfactorily.

1960 August 18 - 19:58 GMT - Cape Canaveral LC17B. Thor Ablestar 262 AB004? FAILURE: Exploded 2.5 minutes after launch. Courier 1A Mass: 225 kg (496 lb). Spacecraft: Courier. Agency: DARPA. Experimental communications sattelite.

1960 September 13 - 22:14 GMT - Vandenberg SLC1E. Thor Agena A 246 / Agena A 1058 Discoverer 15 Mass: 863 kg (1,902 lb). Spacecraft: KH-1. Agency: U.S. Air Force. Perigee: 200 km (120 mi). Apogee: 755 km (469 mi). Inclination: 80.90 deg. Period: 94.10 min. KH-1; film capsule lost at sea. Mission failed. Attained orbit successfully. Capsule sank prior to retrieval.

1960 October 4 - 17:50 GMT - Cape Canaveral LC17B. Thor Ablestar 293 AB005 Courier 1B Mass: 230 kg (500 lb). Spacecraft: Courier. Agency: U.S. Army. Perigee: 967 km (600 mi). Apogee: 1,214 km (754 mi). Inclination: 28.30 deg. Period: 107.10 min. Experimental communications. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1960 October 11 - 21:53 GMT - Vandenberg LE-8. Thor DM-18A 186 Combat training launch Agency: RAF. Apogee: 520 km (320 mi).

1960 October 26 - 20:26 GMT - Vandenberg SLC1W. Thor Agena B 253 / Agena B 1061 FAILURE: Failure. Discoverer 16 Mass: 1,091 kg (2,405 lb). Spacecraft: KH-2. Agency: U.S. Air Force. KH-1; mission failed.

1960 November 12 - 20:43 GMT - Vandenberg SLC1E. Thor Agena B 297 / Agena B 1062 Discoverer 17 Mass: 1,091 kg (2,405 lb). Spacecraft: KH-2. Agency: U.S. Air Force. Perigee: 190 km (110 mi). Apogee: 984 km (611 mi). Inclination: 81.70 deg. Period: 96.40 min. KH-1; film capsule recovered 2.1 days later. Mission failed. Obtained orbit successfully. Film separated before any camera operation leaving only 1.7 ft of film in capsule. On December 2, the Air Force revealed that exceedingly valuable information had been obtained from human tissues carried by Discoverer 17 (the cover story for the mission). The tissues had been exposed to an unexpectedly heavy dose of radiation for more than 50 hours in flight.

1960 November 23 - 11:13 GMT - Cape Canaveral LC17A. Thor Delta 245/D3 Tiros 2 Mass: 130 kg (280 lb). Spacecraft: Tiros. Agency: NASA. Perigee: 547 km (339 mi). Apogee: 610 km (370 mi). Inclination: 48.50 deg. Period: 96.30 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1960 November 30 - 19:50 GMT - Cape Canaveral LC17B. Thor Ablestar 283 AB006 FAILURE: Failure. Transit 3A Mass: 91 kg (200 lb). Spacecraft: Transit. Agency: U.S. Navy. Destroyed by range safety; launched with Solrad 2. Thor shut down too early.

1960 December 7 - 20:20 GMT - Vandenberg SLC1W. Thor Agena B 296 / Agena B 1103 Discoverer 18 Mass: 1,240 kg (2,730 lb). Spacecraft: KH-2. Agency: U.S. Air Force. Perigee: 233 km (144 mi). Apogee: 510 km (310 mi). Inclination: 81.50 deg. Period: 92.00 min. KH-2; film capsule recovered 3.1 days later. First successful mission employing KH-2 camera system.

1960 December 13 - 20:08 GMT - Vandenberg LE-8. Thor DM-18A 267 Combat training launch Agency: RAF. Apogee: 520 km (320 mi).

1960 December 20 - 20:32 GMT - Vandenberg SLC1E. Thor Agena B 258 / Agena B 1101 Discoverer 19 Mass: 1,060 kg (2,330 lb). Spacecraft: Midas. Agency: U.S. Air Force. Perigee: 186 km (115 mi). Apogee: 359 km (223 mi). Inclination: 83.40 deg. Period: 90.00 min. Tested IR sensors for Midas program; did not carry camera or film capsule.

1961 February 17 - 20:25 GMT - Vandenberg SLC1W. Thor Agena B 298 Discoverer 20 Mass: 1,110 kg (2,440 lb). Spacecraft: KH-5. Agency: U.S. Navy. Perigee: 277 km (172 mi). Apogee: 491 km (305 mi). Inclination: 80.80 deg. Period: 92.30 min. KH-5; film capsule not ejected. Mission failed. Program malfunctioned and capsule did not reenter. First attempted ARGON mission. Officially: Spacecraft Engaged in investigation of spaceflight techniques and technology (US Cat A).