Model: Delta.

Delta Credit - (c) Mark Wade

Orbital launch vehicle. Other Family:

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 After a few years the Thors were withdrawn from Britain (and the Jupiters from Turkey) as part of the secret codicil of Kennedy's deal to end the Cuban Missile Crisis.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

Model: 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.

Model: 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.

Model: 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).

Model: 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.

Model: 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.