Scout 2 Credit - ESA

All-solid orbital launch vehicle. Country: USA. Status: Retired 1994.

Solid-fuel, light payload, lower-cost launch vehicle developed by the Air Force and NASA in the late 1950's and used in a variety of configurations over thirty years. Launched from Cape Canaveral, Vandenberg, Wallops Island, and from Italy's equatorial San Marco platform off Kenya. Italy studied but did not develop subsequent upgraded versions.

The Scout was a four-stage, solid-fuelled rocket developed to provide the United States with a reliable, versatile and cost-effective launch vehicle for a variety of space exploration tasks - orbital, high altitude probe, and high speed re-entry. Developed by NASA, the vehicle was produced by LTV Aerospace's Missiles and Space Division, which also provides systems management. The first US solid-propellant rocket capable of placing payloads in orbit, Scout had important roles in the space programs of NASA and the Department of Defense plus those of the United Kingdom, Italy, France, Germany and the 10-nation European Space Research Organisation (ESRO). Scout was launched in the United States from NASA’s Wallops Island, Virginia, and by Air Force crews from the Western Test Range in California. A third site - the Italian San Marco sea-based platform off the east coast of Africa-made possible launches along the equator. Early Scouts were capable of boosting less than 150 kg into a nominal 500-km orbit. Performance was increased by development of a fifth stage velocity package. Prime Contractor: LTV Aerospace Corporation, a subsidiary of Ling-Temco-Vought, Inc. Associate Contractors: Aerojet General (first stage); Thiokol Chemical (second stage); Hercules Powder Company (third stage); United Technology Center (fourth stage); Honeywell (guidance).

Manufacturer: Vought. Launches: 148. Failures: 27. Success Rate: 81.76%. First Launch Date: 1960-04-18. Last Launch Date: 1994-05-09. Launch data is: complete. Version:

Blue Scout Junior. Suborbital launch vehicle. Status: Out of production. Department of Defence Designation: XRM-91.

Smaller Air Force version of Scout used for suborbital military tests.

Historical Essay © Andreas Parsch

Ford RM-91 Blue Scout Junior

The XRM-91 Blue Scout Junior (sometimes called Journeyman B) was a rocket of the U.S. Air Force's System 609A Blue Scout family (for general information on Blue Scout, see article on RM-89 Blue Scout I). The XRM-91 did not resemble the other Scout variants externally, because the usual first Scout stage (an Aerojet General Algol) was not used. Instead, the four-stage Blue Scout Junior used Scout's 2nd and 3rd stages (Castor and Antares) as the first two stages, and added an Aerojet General Alcor and a spherical NOTS Cetus in a common nose fairing. The XRM-91 also lacked the gyro-stabilization and guidance system of the RM-89 Blue Scout I and RM-90 Blue Scout II, making it a completely unguided rocket. It relied on second-stage fins and two spin motors to achieve a stable flight trajectory.

The first launch of an XRM-91 occurred on 21 September 1960, making it actually the first Blue Scout configuration to fly. The flight was planned to make radiation and magnetic field measurements at distances of up to 26700 km (16600 miles) from earth, and while the rocket did indeed achieve this altitude, the telemetry system failed so that no data was received. The second launch in November ended with a failure during second stage burn. The third flight was to measure particle densities in the Van Allen belts and reached a distance of 225000 km (140000 miles), but again a telemetry failure prevented the reception of scientific data. The fourth and final XRM-91 mission in December 1961 also carried particle detectors, and was the only completely successful flight of the initial Blue Scout Junior program. The Blue Scout Junior would have been easily powerful enough to put a small satellite in low-earth orbit but was never used to do so.

The Blue Scout Junior was regarded by the USAF as the most useful of the various Blue Scout configurations. It was used (in slightly modified form) between 1962 and 1965 by the Air Force as the SLV-1B/C launch vehicle for suborbital scientific payloads. The SLV-1C was also chosen as the rocket for the MER-6A interim ERCS (Emergency Rocket Communications System) vehicle. The NASA used a three-stage Blue Scout Junior configuration (omitting the Cetus 4th stage) as the RAM B.

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

Data for XRM-91:

[1] Peter Alway: "Rockets of the World, 2000 Supplement", Saturn Press, 2000
[2] Norman J. Bowman: "The Handbook of Rockets and Guided Missiles", Perastadion Press, 1963
[3] Mark Wade: Encyclopedia Astronautica

Payload: 10 kg (22 lb). to a: 26.775 km altitude, 11,290 km range trajectory. Apogee: 1,000 km (600 mi). Liftoff Thrust: 222.400 kN (49,998 lbf). Total Mass: 5,797 kg (12,780 lb). Core Diameter: 0.79 m (2.59 ft). Total Length: 14.00 m (45.00 ft). Version:

Blue Scout Jr.

Blue Scout Junior Credit - via Peter Alway

Suborbital launch vehicle.

Four stage vehicle consisting of 1 x Castor + 1 x Antares + 1 x Alcor + 1 x Cetus

Launches: 12. Failures: 4. First Launch Date: 1960-09-21. Last Launch Date: 1965-06-09. Apogee: 200,000 km (120,000 mi). Liftoff Thrust: 222.000 kN (49,907 lbf). Total Mass: 5,800 kg (12,700 lb). Core Diameter: 0.79 m (2.59 ft). Total Length: 12.40 m (40.60 ft).

• Stage1: 1 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.

• Stage2: 1 x Antares 1A. Gross Mass: 1,225 kg (2,700 lb). Empty Mass: 294 kg (648 lb). Motor: 1 x X-254. Thrust (vac): 60.497 kN (13,600 lbf). Isp: 256 sec. Burn time: 39 sec. Length: 3.38 m (11.08 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage3: 1 x Alcor. Gross Mass: 520 kg (1,140 lb). Empty Mass: 50 kg (110 lb). Motor: 1 x Alcor. Thrust (vac): 35.588 kN (8,001 lbf). Isp: 230 sec. Burn time: 30 sec. Length: 1.37 m (4.49 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.

• Stage4: 1 x Cetus. Gross Mass: 50 kg (110 lb). Empty Mass: 10 kg (22 lb). Motor: 1 x NOTS 100A. Thrust (vac): 4.001 kN (899 lbf). Isp: 230 sec. Burn time: 20 sec. Length: 0.51 m (1.67 ft). Diameter: 0.43 m (1.41 ft). Propellants: Solid.

Apogee: 1,000 km (600 mi). Liftoff Thrust: 222.000 kN (49,907 lbf). Total Mass: 5,800 kg (12,700 lb). Total Length: 12.00 m (39.00 ft). Version:

Blue Scout ERCS.

Blue Scout ERCS Credit - via Andreas Parsch

Strategic communications missile. Department of Defence Designation: MER-6. Popular Name: Blue Scout ERCS.

USAF initial Emergency Rocket Communications System booster.

Historical Essay © Andreas Parsch

Ford MER-6 Blue Scout ERCS

In September 1961, the Strategic Air Command of the USAF issued a requirement for a rocket-borne UHF communication system in defense emergencies when conventional communication links were disrupted. This system, called ERCS (Emergency Rocket Communications System), was to provide a reliable and survivable connectivity between command posts and launch control centers. The ERCS UHF transmitters carried prerecorded force execution messages that were transmitted to all units within line of sight of a rocket's apogee.

Air Force Program 279L was initiated for deployment of an interim ERCS capability on Ford Aeronutronics XRM-91 Blue Scout Junior rockets. The XRM-91 was a four-stage rocket based on LTV's Scout family of launch vehicles, which first flew on 21 September 1960. Blue Scout Junior rockets and other Scout derivatives were used as launch vehicles by the USAF throughout the 1960s and 1970s under the basic designation of SLV-1 Scout.

The first launch of a Blue Scout Junior rocket equipped with an ERCS occurred on 31 May 1962. In July 1963, the Blue Scout Junior ERCS was declared operational, with rockets based at three locations in Nebraska. Shortly before, in June 1963, the ERCS-equipped Blue Scout Junior had received the designation MER-6A.

The ultimate ERCS used modified LGM-30F Minuteman II missiles as carrier vehicles. The Minuteman ERCS became operational in October 1967, and in December 1967 the MER-6A rockets had been withdrawn from service. The Minuteman ERCS remained operational until the early 1990s.

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

Data for XRM-91 (MER-6A was similar):

[1] Federation of American Scientists Website
[2] Peter Alway: "Rockets of the World, 2000 Supplement", Saturn Press, 2000

Version:

Blue Scout 1. Suborbital launch vehicle. Department of Defence Designation: XRM-89.

Air Force version of Scout used for suborbital tests.

Historical Essay © Andreas Parsch

Ford RM-89 Blue Scout I

In the late 1950s, the NASA established the Scout program to develop a multistage solid-propellant space booster and research rocket. The U.S. Air Force also participated in the program, but different requirements led to some divergence in the development of NASA and USAF Scouts. The USAF Scout program was known as HETS (Hyper Environmental Test System) or System 609A, and the rockets were generally referred to as Blue Scout. The prime contractor for the NASA Scout was LTV, but the Blue Scout prime contractor was Ford Aeronutronics.

The basic NASA Scout configuration, from which all variants were derived, was known as Scout-X1. It was a four-stage rocket, which used the following motors:

• 1st stage: Aerojet General Algol
• 2nd stage: Thiokol XM33 Castor
• 3rd stage: Allegany Ballistics Lab X-254 Antares
• 4th stage: Allegany Ballistics Lab X-248 Altair

The Scout-X1 first flew successfully on 10 October 1960, after an earlier failure in July 1960. The rocket's first stage had four stabilizing fins, and the vehicle incorporated a gyro-based guidance system for attitude stabilization to keep the rocket on course.

By using different combinations of rocket stages, the USAF created several different Blue Scout configurations. One of these was the XRM-89 Blue Scout I, which was a three-stage vehicle, omitting the basic Scout's Altair 4th stage. The first launch of an XRM-89 occurred on 7 January 1961, and was mostly successful. On that flight, the XRM-89 carried a variety of experiments to measure rocket performance and high-altitude fields and particle radiation. The payload was located in a recoverable reentry capsule, but the capsule sunk in the water before it could be recovered. The only other XRM-89 launches (in May 1961 and April 1962) were unsuccessful, and the Blue Scout I program was terminated in 1962.

Other USAF Scout versions were the RM-90 Blue Scout II, the RM-91 Blue Scout Junior (which was by far the most important and successful variant), and the RM-92 Air Force Scout.

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

Data for XRM-89:

[1] Peter Alway: "Rockets of the World, 2000 Supplement", Saturn Press, 2000
[2] Norman J. Bowman: "The Handbook of Rockets and Guided Missiles", Perastadion Press, 1963

Launches: 3. Failures: 2. First Launch Date: 1961-01-07. Last Launch Date: 1962-04-12. Payload: 88 kg (194 lb). to a: 1386 km altitude, 2419 km range trajectory. Apogee: 5,000 km (3,100 mi). Liftoff Thrust: 511.500 kN (114,990 lbf). Total Mass: 16,738 kg (36,900 lb). Core Diameter: 1.02 m (3.34 ft). Total Length: 22.00 m (72.00 ft).

• Stage1: 1 x Algol 1. Gross Mass: 10,705 kg (23,600 lb). Empty Mass: 1,900 kg (4,100 lb). Motor: 1 x Algol 1. Thrust (vac): 470.934 kN (105,870 lbf). Isp: 236 sec. Burn time: 40 sec. Length: 9.12 m (29.92 ft). Diameter: 1.01 m (3.31 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 1A. Gross Mass: 1,225 kg (2,700 lb). Empty Mass: 294 kg (648 lb). Motor: 1 x X-254. Thrust (vac): 60.497 kN (13,600 lbf). Isp: 256 sec. Burn time: 39 sec. Length: 3.38 m (11.08 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

Historical Essay © Andreas Parsch

Ford RM-90 Blue Scout II

The XRM-90 Blue Scout II was a rocket of the U.S. Air Force's System 609A Blue Scout family (for general information on Blue Scout, see article on RM-89 Blue Scout I). The XRM-90 was a four-stage rocket, which used the same stages as the basic NASA Scout. It was nevertheless not identical to the latter, because the 4th stage was hidden in a payload fairing with the same diameter as the 3rd stage, and the first stage nozzle used a flared tail skirt between the fins. Externally, the XRM-90 was indistinguishable from the XRM-89 Blue Scout I.

The first XRM-90 launch occurred on 3 March 1961, followed by a second one on 12 April 1961. Both sub-orbital flights were successful, and measured radiation levels in the Van Allen belts. The second Blue Scout II also carried a micrometeorite sampling experiment, but the recovery of the reentry capsule failed. The third XRM-90 was used by NASA in November 1961 in an attempt to launch a communications payload for Project Mercury into orbit, but this rocket failed. The USAF subsequently abandoned the XRM-89 Blue Scout I and XRM-90 Blue Scout II vehicles, and shifted to the RM-91/SLV-1B Blue Scout Junior instead.

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

Data for XRM-90:

[1] Peter Alway: "Rockets of the World, 2000 Supplement", Saturn Press, 2000
[2] Norman J. Bowman: "The Handbook of Rockets and Guided Missiles", Perastadion Press, 1963
[3] Mark Wade: Encyclopedia Astronautica

Launches: 3. Failures: 1. First Launch Date: 1961-03-03. Last Launch Date: 1961-11-01. LEO Payload: 30 kg (66 lb). to: 300 km Orbit. at: 28.00 degrees. Apogee: 2,500 km (1,500 mi). Liftoff Thrust: 511.500 kN (114,990 lbf). Total Mass: 16,874 kg (37,200 lb). Core Diameter: 1.02 m (3.34 ft). Total Length: 24.00 m (78.00 ft).

• Stage1: 1 x Algol 1. Gross Mass: 10,705 kg (23,600 lb). Empty Mass: 1,900 kg (4,100 lb). Motor: 1 x Algol 1. Thrust (vac): 470.934 kN (105,870 lbf). Isp: 236 sec. Burn time: 40 sec. Length: 9.12 m (29.92 ft). Diameter: 1.01 m (3.31 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 1A. Gross Mass: 1,225 kg (2,700 lb). Empty Mass: 294 kg (648 lb). Motor: 1 x X-254. Thrust (vac): 60.497 kN (13,600 lbf). Isp: 256 sec. Burn time: 39 sec. Length: 3.38 m (11.08 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage4: 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 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.

• Stage2: 1 x Antares 1A. Gross Mass: 1,225 kg (2,700 lb). Empty Mass: 294 kg (648 lb). Motor: 1 x X-254. Thrust (vac): 60.497 kN (13,600 lbf). Isp: 256 sec. Burn time: 39 sec. Length: 3.38 m (11.08 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage3: 1 x Alcor. Gross Mass: 520 kg (1,140 lb). Empty Mass: 50 kg (110 lb). Motor: 1 x Alcor. Thrust (vac): 35.588 kN (8,001 lbf). Isp: 230 sec. Burn time: 30 sec. Length: 1.37 m (4.49 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.

• Stage1: 1 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.

• Stage2: 1 x Antares 1A. Gross Mass: 1,225 kg (2,700 lb). Empty Mass: 294 kg (648 lb). Motor: 1 x X-254. Thrust (vac): 60.497 kN (13,600 lbf). Isp: 256 sec. Burn time: 39 sec. Length: 3.38 m (11.08 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage3: 1 x Alcor. Gross Mass: 520 kg (1,140 lb). Empty Mass: 50 kg (110 lb). Motor: 1 x Alcor. Thrust (vac): 35.588 kN (8,001 lbf). Isp: 230 sec. Burn time: 30 sec. Length: 1.37 m (4.49 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.

• Stage4: 1 x Cetus. Gross Mass: 50 kg (110 lb). Empty Mass: 10 kg (22 lb). Motor: 1 x NOTS 100A. Thrust (vac): 4.001 kN (899 lbf). Isp: 230 sec. Burn time: 20 sec. Length: 0.51 m (1.67 ft). Diameter: 0.43 m (1.41 ft). Propellants: Solid.

• Stage1: 1 x Algol 1. Gross Mass: 10,705 kg (23,600 lb). Empty Mass: 1,900 kg (4,100 lb). Motor: 1 x Algol 1. Thrust (vac): 470.934 kN (105,870 lbf). Isp: 236 sec. Burn time: 40 sec. Length: 9.12 m (29.92 ft). Diameter: 1.01 m (3.31 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 1A. Gross Mass: 1,225 kg (2,700 lb). Empty Mass: 294 kg (648 lb). Motor: 1 x X-254. Thrust (vac): 60.497 kN (13,600 lbf). Isp: 256 sec. Burn time: 39 sec. Length: 3.38 m (11.08 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage4: 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: 7. Failures: 4. First Launch Date: 1960-07-02. Last Launch Date: 1961-10-19. LEO Payload: 59 kg (130 lb). to: 185 km Orbit. Associated Spacecraft: S-55, S-56. Liftoff Thrust: 427.100 kN (96,016 lbf). Total Mass: 16,240 kg (35,800 lb). Core Diameter: 1.01 m (3.31 ft). Total Length: 25.00 m (82.00 ft). Flyaway Unit Cost $: 8.910 million. in: 1985 unit dollars.

• Stage1: 1 x Algol 1. Gross Mass: 10,705 kg (23,600 lb). Empty Mass: 1,900 kg (4,100 lb). Motor: 1 x Algol 1. Thrust (vac): 470.934 kN (105,870 lbf). Isp: 236 sec. Burn time: 40 sec. Length: 9.12 m (29.92 ft). Diameter: 1.01 m (3.31 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 1A. Gross Mass: 1,225 kg (2,700 lb). Empty Mass: 294 kg (648 lb). Motor: 1 x X-254. Thrust (vac): 60.497 kN (13,600 lbf). Isp: 256 sec. Burn time: 39 sec. Length: 3.38 m (11.08 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage4: 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 Algol 1. Gross Mass: 10,705 kg (23,600 lb). Empty Mass: 1,900 kg (4,100 lb). Motor: 1 x Algol 1. Thrust (vac): 470.934 kN (105,870 lbf). Isp: 236 sec. Burn time: 40 sec. Length: 9.12 m (29.92 ft). Diameter: 1.01 m (3.31 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 1A. Gross Mass: 1,225 kg (2,700 lb). Empty Mass: 294 kg (648 lb). Motor: 1 x X-254. Thrust (vac): 60.497 kN (13,600 lbf). Isp: 256 sec. Burn time: 39 sec. Length: 3.38 m (11.08 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage4: 1 x Altair 1A. Gross Mass: 390 kg (850 lb). Empty Mass: 181 kg (399 lb). Motor: 1 x X-248A. Thrust (vac): 13.788 kN (3,100 lbf). Isp: 255 sec. Burn time: 40 sec. Length: 2.50 m (8.20 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.

Launches: 2. Failures: 1. First Launch Date: 1962-03-29. Last Launch Date: 1962-04-26. LEO Payload: 76 kg (167 lb). to: 185 km Orbit. Associated Spacecraft: GRAB, Program 35. Liftoff Thrust: 427.100 kN (96,016 lbf). Total Mass: 16,440 kg (36,240 lb). Core Diameter: 1.01 m (3.31 ft). Total Length: 25.00 m (82.00 ft). Flyaway Unit Cost $: 8.910 million. in: 1985 unit dollars.

• Stage1: 1 x Algol 1D. Gross Mass: 10,700 kg (23,500 lb). Empty Mass: 1,200 kg (2,600 lb). Motor: 1 x Algol ID. Thrust (vac): 440.000 kN (98,910 lbf). Burn time: 44 sec. Length: 9.40 m (30.80 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 2. Gross Mass: 1,400 kg (3,000 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x X-259. Thrust (vac): 93.094 kN (20,928 lbf). Isp: 293 sec. Burn time: 36 sec. Length: 2.90 m (9.50 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage4: 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 Algol 1. Gross Mass: 10,705 kg (23,600 lb). Empty Mass: 1,900 kg (4,100 lb). Motor: 1 x Algol 1. Thrust (vac): 470.934 kN (105,870 lbf). Isp: 236 sec. Burn time: 40 sec. Length: 9.12 m (29.92 ft). Diameter: 1.01 m (3.31 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 2. Gross Mass: 1,400 kg (3,000 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x X-259. Thrust (vac): 93.094 kN (20,928 lbf). Isp: 293 sec. Burn time: 36 sec. Length: 2.90 m (9.50 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage4: 1 x Altair 1A. Gross Mass: 390 kg (850 lb). Empty Mass: 181 kg (399 lb). Motor: 1 x X-248A. Thrust (vac): 13.788 kN (3,100 lbf). Isp: 255 sec. Burn time: 40 sec. Length: 2.50 m (8.20 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.

• Stage1: 1 x Algol 1D. Gross Mass: 10,700 kg (23,500 lb). Empty Mass: 1,200 kg (2,600 lb). Motor: 1 x Algol ID. Thrust (vac): 440.000 kN (98,910 lbf). Burn time: 44 sec. Length: 9.40 m (30.80 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 2. Gross Mass: 1,400 kg (3,000 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x X-259. Thrust (vac): 93.094 kN (20,928 lbf). Isp: 293 sec. Burn time: 36 sec. Length: 2.90 m (9.50 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage4: 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 Algol 1D. Gross Mass: 10,700 kg (23,500 lb). Empty Mass: 1,200 kg (2,600 lb). Motor: 1 x Algol ID. Thrust (vac): 440.000 kN (98,910 lbf). Burn time: 44 sec. Length: 9.40 m (30.80 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 2. Gross Mass: 1,400 kg (3,000 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x X-259. Thrust (vac): 93.094 kN (20,928 lbf). Isp: 293 sec. Burn time: 36 sec. Length: 2.90 m (9.50 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage4: 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.

Launches: 6. Failures: 1. First Launch Date: 1962-12-16. Last Launch Date: 1964-03-27. LEO Payload: 87 kg (191 lb). to: 185 km Orbit. Associated Spacecraft: Ariel, Program 35, S-55, Transit. Liftoff Thrust: 513.400 kN (115,417 lbf). Total Mass: 17,350 kg (38,250 lb). Core Diameter: 1.01 m (3.31 ft). Total Length: 24.00 m (78.00 ft). Flyaway Unit Cost $: 8.910 million. in: 1985 unit dollars.

• Stage1: 1 x Algol 2. Gross Mass: 11,600 kg (25,500 lb). Empty Mass: 1,650 kg (3,630 lb). Motor: 1 x Algol 2. Thrust (vac): 564.245 kN (126,847 lbf). Isp: 255 sec. Burn time: 47 sec. Length: 9.09 m (29.82 ft). Diameter: 1.01 m (3.31 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 2. Gross Mass: 1,400 kg (3,000 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x X-259. Thrust (vac): 93.094 kN (20,928 lbf). Isp: 293 sec. Burn time: 36 sec. Length: 2.90 m (9.50 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage4: 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 Algol 2. Gross Mass: 11,600 kg (25,500 lb). Empty Mass: 1,650 kg (3,630 lb). Motor: 1 x Algol 2. Thrust (vac): 564.245 kN (126,847 lbf). Isp: 255 sec. Burn time: 47 sec. Length: 9.09 m (29.82 ft). Diameter: 1.01 m (3.31 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 2. Gross Mass: 1,400 kg (3,000 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x X-259. Thrust (vac): 93.094 kN (20,928 lbf). Isp: 293 sec. Burn time: 36 sec. Length: 2.90 m (9.50 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage4: 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.

• Stage5: 1 x Cetus. Gross Mass: 50 kg (110 lb). Empty Mass: 10 kg (22 lb). Motor: 1 x NOTS 100A. Thrust (vac): 4.001 kN (899 lbf). Isp: 230 sec. Burn time: 20 sec. Length: 0.51 m (1.67 ft). Diameter: 0.43 m (1.41 ft). Propellants: Solid.

• Stage1: 1 x Algol 2. Gross Mass: 11,600 kg (25,500 lb). Empty Mass: 1,650 kg (3,630 lb). Motor: 1 x Algol 2. Thrust (vac): 564.245 kN (126,847 lbf). Isp: 255 sec. Burn time: 47 sec. Length: 9.09 m (29.82 ft). Diameter: 1.01 m (3.31 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 2. Gross Mass: 1,400 kg (3,000 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x X-259. Thrust (vac): 93.094 kN (20,928 lbf). Isp: 293 sec. Burn time: 36 sec. Length: 2.90 m (9.50 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage4: 1 x Altair 1A. Gross Mass: 390 kg (850 lb). Empty Mass: 181 kg (399 lb). Motor: 1 x X-248A. Thrust (vac): 13.788 kN (3,100 lbf). Isp: 255 sec. Burn time: 40 sec. Length: 2.50 m (8.20 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.

• Stage1: 1 x Algol 2. Gross Mass: 11,600 kg (25,500 lb). Empty Mass: 1,650 kg (3,630 lb). Motor: 1 x Algol 2. Thrust (vac): 564.245 kN (126,847 lbf). Isp: 255 sec. Burn time: 47 sec. Length: 9.09 m (29.82 ft). Diameter: 1.01 m (3.31 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 2. Gross Mass: 1,400 kg (3,000 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x X-259. Thrust (vac): 93.094 kN (20,928 lbf). Isp: 293 sec. Burn time: 36 sec. Length: 2.90 m (9.50 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage4: 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.

Launches: 13. Failures: 1. First Launch Date: 1963-06-28. Last Launch Date: 1965-12-06. LEO Payload: 103 kg (227 lb). to: 185 km Orbit. Associated Spacecraft: ADE, Beacon, ESRS, FRANCE, GRS, IE, Injun, IQSY, S-55, San Marco, Transit. Liftoff Thrust: 513.400 kN (115,417 lbf). Total Mass: 17,250 kg (38,020 lb). Core Diameter: 1.01 m (3.31 ft). Total Length: 25.00 m (82.00 ft). Flyaway Unit Cost $: 8.610 million. in: 1985 unit dollars.

• Stage1: 1 x Algol 2. Gross Mass: 11,600 kg (25,500 lb). Empty Mass: 1,650 kg (3,630 lb). Motor: 1 x Algol 2. Thrust (vac): 564.245 kN (126,847 lbf). Isp: 255 sec. Burn time: 47 sec. Length: 9.09 m (29.82 ft). Diameter: 1.01 m (3.31 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 2. Gross Mass: 1,400 kg (3,000 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x X-259. Thrust (vac): 93.094 kN (20,928 lbf). Isp: 293 sec. Burn time: 36 sec. Length: 2.90 m (9.50 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage4: 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 Algol 2. Gross Mass: 11,600 kg (25,500 lb). Empty Mass: 1,650 kg (3,630 lb). Motor: 1 x Algol 2. Thrust (vac): 564.245 kN (126,847 lbf). Isp: 255 sec. Burn time: 47 sec. Length: 9.09 m (29.82 ft). Diameter: 1.01 m (3.31 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 2. Gross Mass: 1,400 kg (3,000 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x X-259. Thrust (vac): 93.094 kN (20,928 lbf). Isp: 293 sec. Burn time: 36 sec. Length: 2.90 m (9.50 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage4: 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 Algol 2B. Gross Mass: 10,700 kg (23,500 lb). Empty Mass: 1,170 kg (2,570 lb). Motor: 1 x Algol IIB. Thrust (vac): 400.000 kN (89,920 lbf). Burn time: 80 sec. Length: 9.10 m (29.80 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 2. Gross Mass: 1,400 kg (3,000 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x X-259. Thrust (vac): 93.094 kN (20,928 lbf). Isp: 293 sec. Burn time: 36 sec. Length: 2.90 m (9.50 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

Launches: 11. First Launch Date: 1965-12-22. Last Launch Date: 1970-08-27. LEO Payload: 122 kg (268 lb). to: 185 km Orbit. Associated Spacecraft: Ariel, Owl, Transit. Liftoff Thrust: 513.400 kN (115,417 lbf). Total Mass: 17,850 kg (39,350 lb). Core Diameter: 1.01 m (3.31 ft). Total Length: 25.00 m (82.00 ft). Flyaway Unit Cost $: 8.610 million. in: 1985 unit dollars.

• Stage1: 1 x Algol 2. Gross Mass: 11,600 kg (25,500 lb). Empty Mass: 1,650 kg (3,630 lb). Motor: 1 x Algol 2. Thrust (vac): 564.245 kN (126,847 lbf). Isp: 255 sec. Burn time: 47 sec. Length: 9.09 m (29.82 ft). Diameter: 1.01 m (3.31 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 2. Gross Mass: 1,400 kg (3,000 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x X-259. Thrust (vac): 93.094 kN (20,928 lbf). Isp: 293 sec. Burn time: 36 sec. Length: 2.90 m (9.50 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage4: 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 Algol 2. Gross Mass: 11,600 kg (25,500 lb). Empty Mass: 1,650 kg (3,630 lb). Motor: 1 x Algol 2. Thrust (vac): 564.245 kN (126,847 lbf). Isp: 255 sec. Burn time: 47 sec. Length: 9.09 m (29.82 ft). Diameter: 1.01 m (3.31 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 2. Gross Mass: 1,400 kg (3,000 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x X-259. Thrust (vac): 93.094 kN (20,928 lbf). Isp: 293 sec. Burn time: 36 sec. Length: 2.90 m (9.50 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage4: 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.

Launches: 25. Failures: 4. First Launch Date: 1965-08-10. Last Launch Date: 1971-11-15. LEO Payload: 143 kg (315 lb). to: 185 km Orbit. Associated Spacecraft: ADE, Ariel, AZUR, Eole, ESRO, Injun, OFO, OV3, P 76, RM, San Marco, SAS, SECOR, Solrad, SSS, TIP. Liftoff Thrust: 513.400 kN (115,417 lbf). Total Mass: 17,900 kg (39,400 lb). Core Diameter: 1.01 m (3.31 ft). Total Length: 25.00 m (82.00 ft). Flyaway Unit Cost $: 8.660 million. in: 1985 unit dollars.

• Stage1: 1 x Algol 2B. Gross Mass: 10,700 kg (23,500 lb). Empty Mass: 1,170 kg (2,570 lb). Motor: 1 x Algol IIB. Thrust (vac): 400.000 kN (89,920 lbf). Burn time: 80 sec. Length: 9.10 m (29.80 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 2. Gross Mass: 1,400 kg (3,000 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x X-259. Thrust (vac): 93.094 kN (20,928 lbf). Isp: 293 sec. Burn time: 36 sec. Length: 2.90 m (9.50 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage4: 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 Algol 2. Gross Mass: 11,600 kg (25,500 lb). Empty Mass: 1,650 kg (3,630 lb). Motor: 1 x Algol 2. Thrust (vac): 564.245 kN (126,847 lbf). Isp: 255 sec. Burn time: 47 sec. Length: 9.09 m (29.82 ft). Diameter: 1.01 m (3.31 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 2. Gross Mass: 1,400 kg (3,000 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x X-259. Thrust (vac): 93.094 kN (20,928 lbf). Isp: 293 sec. Burn time: 36 sec. Length: 2.90 m (9.50 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage4: 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 Algol 2. Gross Mass: 11,600 kg (25,500 lb). Empty Mass: 1,650 kg (3,630 lb). Motor: 1 x Algol 2. Thrust (vac): 564.245 kN (126,847 lbf). Isp: 255 sec. Burn time: 47 sec. Length: 9.09 m (29.82 ft). Diameter: 1.01 m (3.31 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 2. Gross Mass: 1,400 kg (3,000 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x X-259. Thrust (vac): 93.094 kN (20,928 lbf). Isp: 293 sec. Burn time: 36 sec. Length: 2.90 m (9.50 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage4: 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 Algol 2C. Gross Mass: 10,800 kg (23,800 lb). Empty Mass: 1,200 kg (2,600 lb). Motor: 1 x Algol IIC. Thrust (vac): 436.000 kN (98,016 lbf). Burn time: 76 sec. Length: 9.10 m (29.80 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 2. Gross Mass: 1,400 kg (3,000 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x X-259. Thrust (vac): 93.094 kN (20,928 lbf). Isp: 293 sec. Burn time: 36 sec. Length: 2.90 m (9.50 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage4: 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.

LEO Payload: 185 kg (407 lb). to: 185 km Orbit. Associated Spacecraft: AEM, Aeros, ANS, Ariel, ESRO, Hawkeye, HILAT, Miranda, MTS, SAGE, San Marco, SAS, TIP, Transit. Liftoff Thrust: 395.500 kN (88,912 lbf). Total Mass: 20,670 kg (45,560 lb). Core Diameter: 1.14 m (3.74 ft). Total Length: 25.00 m (82.00 ft). Flyaway Unit Cost $: 8.660 million. in: 1985 unit dollars. Version:

Scout D-1.

Four stage vehicle consisting of 1 x Algol 3A + 1 x Castor 2 + 1 x Antares 2 + 1 x Star 20

Launches: 16. Failures: 1. First Launch Date: 1972-08-13. Last Launch Date: 1983-06-27. LEO Payload: 183 kg (403 lb). Apogee: 10,000 km (6,000 mi). Liftoff Thrust: 464.000 kN (104,311 lbf). Total Mass: 20,600 kg (45,400 lb). Core Diameter: 1.14 m (3.74 ft). Total Length: 25.00 m (82.00 ft).

• Stage1: 1 x Algol 3. Gross Mass: 14,320 kg (31,570 lb). Empty Mass: 1,600 kg (3,500 lb). Motor: 1 x Algol 3. Thrust (vac): 471.905 kN (106,088 lbf). Isp: 284 sec. Burn time: 75 sec. Length: 9.40 m (30.80 ft). Diameter: 1.14 m (3.74 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 2. Gross Mass: 1,400 kg (3,000 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x X-259. Thrust (vac): 93.094 kN (20,928 lbf). Isp: 293 sec. Burn time: 36 sec. Length: 2.90 m (9.50 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage4: 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 Algol 3A. Gross Mass: 14,732 kg (32,478 lb). Empty Mass: 2,030 kg (4,470 lb). Motor: 1 x Algol 3A. Thrust (vac): 464.707 kN (104,470 lbf). Isp: 259 sec. Burn time: 84 sec. Length: 9.40 m (30.80 ft). Diameter: 1.14 m (3.74 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 2. Gross Mass: 1,400 kg (3,000 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x X-259. Thrust (vac): 93.094 kN (20,928 lbf). Isp: 293 sec. Burn time: 36 sec. Length: 2.90 m (9.50 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage4: 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 Algol 3A. Gross Mass: 14,732 kg (32,478 lb). Empty Mass: 2,030 kg (4,470 lb). Motor: 1 x Algol 3A. Thrust (vac): 464.707 kN (104,470 lbf). Isp: 259 sec. Burn time: 84 sec. Length: 9.40 m (30.80 ft). Diameter: 1.14 m (3.74 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 2. Gross Mass: 1,400 kg (3,000 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x X-259. Thrust (vac): 93.094 kN (20,928 lbf). Isp: 293 sec. Burn time: 36 sec. Length: 2.90 m (9.50 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage4: 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.

• Stage5: 1 x SPARTA-3. Gross Mass: 100 kg (220 lb). Empty Mass: 28 kg (61 lb). Motor: 1 x BE-3. Thrust (vac): 34.000 kN (7,643 lbf). Burn time: 9.00 sec. Length: 0.60 m (1.96 ft). Diameter: 0.60 m (1.96 ft). Propellants: Solid.

Launches: 2. Failures: 1. First Launch Date: 1975-05-07. Last Launch Date: 1975-12-06. LEO Payload: 193 kg (425 lb). to: 185 km Orbit. Apogee: 500 km (310 mi). Associated Spacecraft: DAD, SAS. Liftoff Thrust: 395.500 kN (88,912 lbf). Total Mass: 20,680 kg (45,590 lb). Core Diameter: 1.14 m (3.74 ft). Total Length: 25.00 m (82.00 ft). Flyaway Unit Cost $: 8.660 million. in: 1985 unit dollars.

• Stage1: 1 x Algol 3. Gross Mass: 14,320 kg (31,570 lb). Empty Mass: 1,600 kg (3,500 lb). Motor: 1 x Algol 3. Thrust (vac): 471.905 kN (106,088 lbf). Isp: 284 sec. Burn time: 75 sec. Length: 9.40 m (30.80 ft). Diameter: 1.14 m (3.74 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 2. Gross Mass: 1,400 kg (3,000 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x X-259. Thrust (vac): 93.094 kN (20,928 lbf). Isp: 293 sec. Burn time: 36 sec. Length: 2.90 m (9.50 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage4: 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.

Launches: 17. First Launch Date: 1979-10-30. Last Launch Date: 1994-05-09. LEO Payload: 210 kg (460 lb). to: 185 km Orbit. Apogee: 1,000 km (600 mi). Associated Spacecraft: ASAT Target Balloon, Macsat, Magsat, MSTI, Nova, Polar Bear, Radcal, REX, SAMPEX, San Marco, Transit. Liftoff Thrust: 395.500 kN (88,912 lbf). Total Mass: 20,930 kg (46,140 lb). Core Diameter: 1.14 m (3.74 ft). Total Length: 26.00 m (85.00 ft). Flyaway Unit Cost $: 8.660 million. in: 1985 unit dollars.

• Stage1: 1 x Algol 3. Gross Mass: 14,320 kg (31,570 lb). Empty Mass: 1,600 kg (3,500 lb). Motor: 1 x Algol 3. Thrust (vac): 471.905 kN (106,088 lbf). Isp: 284 sec. Burn time: 75 sec. Length: 9.40 m (30.80 ft). Diameter: 1.14 m (3.74 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Antares 3A. Gross Mass: 1,637 kg (3,608 lb). Empty Mass: 352 kg (776 lb). Motor: 1 x X-259A. Thrust (vac): 80.796 kN (18,164 lbf). Isp: 295 sec. Burn time: 48 sec. Length: 3.51 m (11.51 ft). Diameter: 0.76 m (2.49 ft). Propellants: Solid.

• Stage4: 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 Scout II TV-1. Gross Mass: 17,300 kg (38,100 lb). Empty Mass: 1,500 kg (3,300 lb). Motor: 1 x Zefiro. Thrust (vac): 590.000 kN (132,630 lbf). Burn time: 71 sec. Length: 4.90 m (16.00 ft). Diameter: 1.14 m (3.74 ft). Propellants: Solid.

• Stage0: 2 x Ariane 3-0. Gross Mass: 9,663 kg (21,303 lb). Empty Mass: 2,313 kg (5,099 lb). Motor: 1 x SPB 7.35. Thrust (vac): 689.990 kN (155,116 lbf). Isp: 263 sec. Burn time: 29 sec. Length: 8.32 m (27.29 ft). Diameter: 1.07 m (3.51 ft). Propellants: Solid.

• Stage1: 1 x Algol 3. Gross Mass: 14,320 kg (31,570 lb). Empty Mass: 1,600 kg (3,500 lb). Motor: 1 x Algol 3. Thrust (vac): 471.905 kN (106,088 lbf). Isp: 284 sec. Burn time: 75 sec. Length: 9.40 m (30.80 ft). Diameter: 1.14 m (3.74 ft). Propellants: Solid.

• Stage2: 1 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.

• Stage3: 1 x Mage 2. Gross Mass: 530 kg (1,160 lb). Empty Mass: 40 kg (88 lb). Motor: 1 x Mage 2. Thrust (vac): 45.483 kN (10,225 lbf). Isp: 293 sec. Burn time: 44 sec. Length: 1.52 m (4.98 ft). Diameter: 0.77 m (2.52 ft). Propellants: Solid.

• Stage4: 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.

1957 July - Beginning of the Scout launch vehicle concept. A study was initiated by the Langley Aeronautical Laboratory on the use of solid-fuel upper stages to achieve a payload orbit with as simple a launch vehicle as possible. This was the beginning of the Scout test-vehicle concept.

1959 March 1 - Scout development begun. "Poor man's rocket," Scout, was jointly announced by NASA and AF. The concept of Scout originated at Langley Research Center in 1958, based upon extensive experience with staged solid-propellant rockets.

1960 April 18 - 23:09 GMT - Wallops Island LA3. Scout X SX-1 FAILURE: Vehicle broke up after first-stage burnout. Cub Scout test Agency: NASA. Apogee: 48 km (29 mi). Scout test vehicle, with live first and third stages. Suborbital.

1960 July 2 - 00:04 GMT - Wallops Island LA3. Scout X-1 ST-1 FAILURE: Failure. Test mission Agency: NASA. Apogee: 1,380 km (850 mi).

1960 September 21 - 13:01 GMT - Cape Canaveral LC18A. Blue Scout Jr D-1 Blue Scout first launch, with Radiation Probe (HETS) payload. Agency: USAF. Apogee: 26,700 km (16,500 mi). USAF Blue Scout rocket fired from Cape Canaveral placed instrumented payload 16,600 miles above the earth, the first of 11 such tests, but no data were received due to radio malfunction.

1960 October 4 - 15:23 GMT - Wallops Island LA3. Scout X-1 ST-2 Radiation Probe Plasma mission Agency: NASA. Apogee: 5,600 km (3,400 mi).

1960 November 8 - 13:18 GMT - Cape Canaveral LC18A. Blue Scout Jr D-2 FAILURE: Failure. HETS Magnetospheric mission Agency: USAF. Apogee: 200 km (120 mi).

1960 December 4 - 21:14 GMT - Wallops Island LA3. Scout X-1 ST-3 FAILURE: Second stage malfunction. Explorer (9) S 56 Mass: 6.00 kg (13.20 lb). Spacecraft: S-56. Agency: NASA.

1961 January 7 - 17:33 GMT - Cape Canaveral LC18B. LV Model: Blue Scout 1 . Blue Scout I D-3 HETS A1-1 Plasma / radio astronomy mission Agency: USAF. Apogee: 1,600 km (900 mi).

1961 February 16 - 13:05 GMT - Wallops Island LA3. Scout X-1 ST-4 Explorer 9 Mass: 7.00 kg (15.40 lb). Spacecraft: S-56. Agency: U.S. Air Force. Perigee: 757 km (470 mi). Apogee: 2,433 km (1,511 mi). Inclination: 38.80 deg. Period: 118.00 min. 12 foot dia. balloon; atmospheric density studies. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1961 March 3 - 16:02 GMT - Cape Canaveral LC18B. LV Model: Blue Scout 2 . Blue Scout II D-4 HETS A2-1 Plasma mission Agency: USAF. Apogee: 2,540 km (1,570 mi).

1961 April 12 - 06:07 GMT - Cape Canaveral LC18B. LV Model: Blue Scout 2 . Blue Scout II D-5 HETS A2-2 Plasma mission Agency: USAF. Apogee: 1,931 km (1,199 mi).

1961 May 5 - Scout to evaluate the Mercury tracking system. Spacecraft: Radio Test Spacecraft. A document was issued regarding use of a Scout test vehicle to evaluate the performance of the Mercury tracking and real-time computing system. NASA Headquarters tentatively approved the plan on May 24, 1961.

1961 May 9 - 16:00 GMT - Cape Canaveral LC18B. LV Model: Blue Scout 1 . Blue Scout I D-6 FAILURE: Failure. HETS A1-2 Plasma mission Agency: USAF. Apogee: 10 km (6 mi).

1961 June 13 - Mercury-Scout instrumentation system. Spacecraft: Radio Test Spacecraft. The Space Task Group forwarded to NASA Headquarters the details for the Mercury-Scout instrumentation system. This mission was to check the operational effectiveness of the Mercury global tracking network.

1961 June 30 - 17:09 GMT - Wallops Island LA3. Scout X-1 ST-5 FAILURE: Third stage did not ignite, and the vehicle was destroyed. Explorer (13) S 55 Mass: 84 kg (185 lb). Spacecraft: S-55. Agency: NASA. Apogee: 172 km (106 mi). Micrometeorite counter satellite (S-55).

1961 August 17 - 14:29 GMT - Cape Canaveral LC18A. Blue Scout Jr O-1 HETS Magnetosphere mission Agency: USAF. Apogee: 225,000 km (139,000 mi).

1961 August 25 - 18:29 GMT - Wallops Island LA3. Scout X-1 ST-6 FAILURE: Partial Failure. Explorer 13 Mass: 86 kg (189 lb). Spacecraft: S-55. Agency: NASA. Perigee: 125 km (77 mi). Apogee: 1,164 km (723 mi). Inclination: 37.70 deg. Period: 97.50 min. Useless orbit; micrometeoroid research. Partial Failure.

1961 October 19 - 17:38 GMT - Wallops Island LA3. Scout X-1 ST-7 P-21 Plasma / aeronomy mission Agency: NASA. Apogee: 6,855 km (4,259 mi).

1961 October 29 - Mercury-Scout announcement Spacecraft: Radio Test Spacecraft. An announcement was made that a Mercury-Scout launch would be made to verify the readiness of the world-wide Mercury Tracking network to handle further orbital flights.

1961 November 1 - 15:32 GMT - Cape Canaveral LC18B. LV Model: Blue Scout 2 . Blue Scout II D-8 FAILURE: Failure. Mercury MS-1 Spacecraft: Radio Test Spacecraft. Agency: USAF. Small satellite was to have verified the readiness of the worldwide Mercury tracking network. An attempt was made to launch Mercury-Scout 1 (MS-1) into orbit with a communications package further to qualify the radar tracking of the Mercury global network prior to manned orbital flight. Shortly after lift-off, the launch vehicle developed erratic motions and attending high aerodynamic loads, and was destroyed by the Range Safety Officer after 43 seconds of flight. No further attempts were planned. The Mercury-Atlas 4 (MA-4) mission and the successful Mercury-Atlas 5 (MA-5), flown on November 29, 1961, disclosed that the network met all requirements.

1961 December 4 - 04:00 GMT - Vandenberg LC-A. Blue Scout Jr O-2 Magnetosphere mission Agency: USAF. Apogee: 44,400 km (27,500 mi).

1962 March 1 - 05:07 GMT - Wallops Island LA3. Scout X-1A ST-8 Reentry 1 re-entry vehicle test flight Agency: NASA. Apogee: 214 km (132 mi).

1962 March 29 - 07:27 GMT - Wallops Island LA3. Scout X-2-1C ST-9 P-21A Plasma / aeronomy mission Agency: NASA. Apogee: 6,291 km (3,909 mi).

1962 April 12 - 16:00 GMT - Cape Canaveral LC18B. LV Model: Blue Scout 1 . Blue Scout I D-7 FAILURE: Failure. Reentry Test re-entry vehicle test flight Agency: USAF. Apogee: 30 km (18 mi).

1962 April 26 - Vandenberg SLC5. Scout X-2 S111 FAILURE: Failure. Solrad 4B Mass: 91 kg (200 lb). Spacecraft: GRAB. Agency: U.S. Navy. Solar radiation monitor.

1962 May 24 - Vandenberg SLC5. Scout X-2M S112 FAILURE: Failure. P 35-1 Spacecraft: Program 35. Agency: AFSC. Military weather satellite to provide targetting information for reconnaisance satellites.

1962 May 31 - 17:08 GMT - Vandenberg LC-A. Blue Scout Jr SLV-1C 102 ERCS/279L 1 Communications mission Agency: USAF. Apogee: 830 km (510 mi).

1962 July 24 - 17:29 GMT - Vandenberg LC-A. Blue Scout Jr SLV-1C 101 ERCS / 279L 2 Communications mission Agency: USAF. Apogee: 1,000 km (600 mi).

1962 August 23 - 11:44 GMT - Vandenberg SLC5. Scout X-2M S117 P 35-2 Mass: 91 kg (200 lb). Spacecraft: Program 35. Agency: U.S. Air Force. Perigee: 578 km (359 mi). Apogee: 752 km (467 mi). Inclination: 98.50 deg. Period: 98.10 min. Military weather satellite to provide targetting information for reconnaisance satellites.

1962 August 31 - Wallops Island LA3. Scout X-3A S114 FAILURE: Late stage 3 ignition. Reentry 2 Agency: NASA. Apogee: 217 km (134 mi).

1962 November 21 - 18:20 GMT - Vandenberg LC-A. Blue Scout Jr SLV-1C 201 ERCS / 279L 3 Communications mission Agency: USAF. Apogee: 1,000 km (600 mi).

1962 December 16 - 14:33 GMT - Wallops Island LA3. Scout X-3 S115 Explorer 16 Mass: 100 kg (220 lb). Spacecraft: S-55. Agency: NASA. Perigee: 744 km (462 mi). Apogee: 1,159 km (720 mi). Inclination: 52.00 deg. Period: 104.10 min. Micrometeoroid data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1962 December 19 - Vandenberg LC-A. Blue Scout Jr SLV-1B(m) 21-1 Ion Engine Test A Technology mission Agency: USAF. Apogee: 2,000 km (1,200 mi). When the high-voltage power supplies were first turned-on, intermittent high-voltage breakdowns occurred, and the beam power supply became inoperative. Post-flight examination of the power supply indicated the high-voltage breakdowns were probably caused by pressure buildup in the primary propulsion unit due to gas vented from the spacecraft batteries. The primary propulsion unit high voltage section was not adequately vented to keep the pressure low enough. Engine thrusting was not accomplished in this test.

1962 December 19 - 01:25 GMT - Vandenberg SLC5. Scout X-3 S118 Transit 5A Mass: 61 kg (134 lb). Spacecraft: Transit. Agency: U.S. Navy. Perigee: 336 km (208 mi). Apogee: 347 km (215 mi). Inclination: 90.60 deg. Period: 91.40 min. First operational solar-powered prototype; failed first day. The satellite verified a new technique for deploying the solar panels and for separating from the rocket, but otherwise it was not successful because of trouble with the power system.

1963 February 2 - 06:56 GMT - Vandenberg LC-A. Blue Scout Jr SLV-1C 202 ERCS 279L Communications mission Agency: USAF. Apogee: 1,000 km (600 mi).

1963 February 19 - 16:33 GMT - Vandenberg SLC5. Scout X-3M S126 P 35-3 Mass: 40 kg (88 lb). Spacecraft: Program 35. Agency: USAF. Perigee: 488 km (303 mi). Apogee: 810 km (500 mi). Inclination: 100.50 deg. Period: 97.80 min. Military weather satellite to provide targetting information for reconnaisance satellites.

1963 March 14 - 01:01 GMT - Vandenberg LC-A. Blue Scout Jr SLV-1C 203 ERCS 279L Communications mission Agency: USAF. Apogee: 1,000 km (600 mi).

1963 April 5 - 03:01 GMT - Vandenberg SLC5. Scout X-3 S119 FAILURE: Failure. Transit 5A-2 Mass: 84 kg (185 lb). Spacecraft: Transit. Agency: U.S. Air Force. Replacement for the failed Transit 5A; failed to reach orbit.

1963 April 26 - Vandenberg SLC5. Scout X-2M S121 FAILURE: Failure. P 35-4 Spacecraft: Program 35. Agency: U.S. Air Force. Military weather satellite to provide targetting information for reconnaisance satellites.

1963 May 17 - 23:00 GMT - Vandenberg LC-A. Blue Scout Jr SLV-1C 301 ERCS 279L Communications mission Agency: USAF. Apogee: 1,000 km (600 mi).

1963 May 22 - 04:38 GMT - Wallops Island LA3. Scout X-3 S116 RFD-1 re-entry vehicle test flight Agency: NASA. Apogee: 145 km (90 mi).

1963 June 16 - 01:49 GMT - Vandenberg SLC5. Scout X-3 S120 Transit 5A-3 Mass: 55 kg (121 lb). Spacecraft: Transit. Agency: USN. Perigee: 350 km (210 mi). Apogee: 360 km (220 mi). Inclination: 89.80 deg. Period: 91.60 min. First operational prototype with a redesigned power supply. A malfunction of the memory occurred during powered flight that kept it from accepting and storing navigation messages, and the oscillator stability was degraded during launch. The satellite could not be used for navigation, but it was the first to achieve gravity-gradient stabilization, and its other subsystems performed well.

1963 June 28 - 21:19 GMT - Wallops Island LA3. Scout X-4 S113 GRS Mass: 99 kg (218 lb). Spacecraft: GRS. Agency: USAF AFC. Perigee: 413 km (256 mi). Apogee: 1,306 km (811 mi). Inclination: 49.70 deg. Period: 102.10 min. Geophysical Research Satellite; space gas data. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

1963 July 20 - 05:44 GMT - Wallops Island LA3. Scout X-3A S110 FAILURE: Failure. Reentry 3 re-entry vehicle test flight Agency: NASA. Apogee: 2.00 km (1.20 mi). NASA launched a Scout rocket with a nose cone of experimental heatshield material from Wallops Island, Va. The rocket was intentionally destroyed when it deviated from its course a few seconds after liftoff. The nose cone had been expected to reenter the atmosphere at 27,934 kilometers (18,600 miles) per hour to test the material's thermal performance under heating loads near those of a lunar reentry.

1963 July 30 - 16:16 GMT - Cape Canaveral LC18A. Blue Scout Jr 22-1/AD-622 OAR 22-1 / AFCRL-1 / 21 Plasma / radio astronomy mission Agency: USAF. Apogee: 11,100 km (6,800 mi).

1963 September 27 - 11:17 GMT - Vandenberg SLC5. Scout X-2B S132 FAILURE: Failure. P 35-5 Mass: 40 kg (88 lb). Spacecraft: Program 35. Agency: U.S. Air Force. Military weather satellite to provide targetting information for reconnaisance satellites.

1963 December 17 - 17:17 GMT - Vandenberg 4300C. Blue Scout Jr SLV-1C 302 ERCS 279L Communications mission Agency: USAF. Apogee: 1,000 km (600 mi).

1963 December 19 - 18:49 GMT - Vandenberg SLC5. Scout X-4 S122R Explorer 19 Mass: 7.00 kg (15.40 lb). Spacecraft: ADE. Agency: NASA LaR. Perigee: 597 km (370 mi). Apogee: 2,391 km (1,485 mi). Inclination: 78.60 deg. Period: 115.90 min. 12 foot dia. balloon; identical to Explorer 9; atmospheric density studies. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1964 March 13 - 11:40 GMT - Cape Canaveral LC18A. Blue Scout Jr 22-2/AD-623 FAILURE: Failure. OAR 22-2 / AFCRL-9 Magnetosphere mission Agency: USAF. Apogee: 600 km (370 mi).

1964 March 27 - 17:25 GMT - Wallops Island LA3. Scout X-3 S127R Ariel 2 Mass: 68 kg (149 lb). Spacecraft: Ariel. Agency: UK DSIR. Perigee: 287 km (178 mi). Apogee: 1,349 km (838 mi). Inclination: 51.70 deg. Period: 101.30 min. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1964 June 4 - 03:50 GMT - Vandenberg SLC5. Scout X-4 S125R Transit 5C-1 Mass: 54 kg (119 lb). Spacecraft: Transit. Agency: USN. Perigee: 825 km (512 mi). Apogee: 898 km (557 mi). Inclination: 90.50 deg. Period: 102.20 min. Operational prototype similar to the 5A series but with some redesign to improve performance. Operated successfully until 23 August 1965.

1964 June 25 - 01:40 GMT - Vandenberg SLC5. Scout X-4 S128R FAILURE: Second stage exploded. ESRS Mass: 79 kg (174 lb). Spacecraft: ESRS. Agency: U.S. Air Force. Environmental Sciences Research Satellite.

1964 July 20 - 10:53 GMT - Wallops Island LA3A. Scout X-4 S124R SERT 1 Technology mission Agency: NASA. Apogee: 4,002 km (2,486 mi). Suborbital 30 minute test of NASA SERT ion engine. The early part of the flight was dedicated to attempts to operate the cesium engine. The cesium engine could not be started because of a high-voltage electrical short circuit. The mercury engine was started about 14 minutes into the flight. This engine was successfully operated for 31 minutes with 53 high-voltage recycle vents which were handled by the fault protection system. Each of the recycle events was only a few seconds duration. Major results from the test were the first demonstration of an ion engine in space, demonstration of effective ion beam neutralization, no EMI effects on other spacecraft systems, and effective recovery from electrical breakdowns. Thrust was measured using three independent measuring systems, and there were no major differences between in-space and ground test performance.

1964 August 18 - 06:05 GMT - Wallops Island LA3. Scout X-4A S129R Reentry 4A Agency: NASA. Apogee: 183 km (113 mi). Scout launch tested Apollo-type ablator materials at lunar reentry heating levels.

1964 August 25 - 13:43 GMT - Vandenberg SLC5. Scout X-4 S134R Explorer 20 Mass: 44 kg (97 lb). Spacecraft: IE. Agency: NASA GSF. Perigee: 857 km (532 mi). Apogee: 999 km (620 mi). Inclination: 79.90 deg. Period: 103.60 min. Ionospheric research. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1964 August 29 - 09:36 GMT - Vandenberg LC-A. Blue Scout Jr SLV-1B(m) 21-2 Ion Engine Test B Technology mission Agency: USAF. Apogee: 2,000 km (1,200 mi). The launch was designed to provide about 30 minutes of flight above an altitude of 370 km. At seven minutes into the flight the engine was operated with ion beam extraction. Full beam current of 94 mA was achieved about 10 minutes later. During the course of engine operation, an electric field strength meter was used to infer payload floating potential relative to space. Spacecraft potential was about 1000 V negative during most of the engine operation with the filament neutralizer. The absolute value of payload potential was about ten times higher than anticipated, and it was suspected that there was inadequate neutralization of the ion beam. The contact ion engine operated for 19 minutes until spacecraft reentry into the atmosphere. In addition to withstanding the environmental rigors of space flight, the ion propulsion system demonstrated electromagnetic compatibility with other spacecraft subsystems and the ability to regulate and control a desired thrust level.

1964 October 9 - 04:04 GMT - Wallops Island LA3A. Scout X-3C S130R RFD-2 re-entry vehicle test flight Agency: NASA. Apogee: 132 km (82 mi).

1964 October 10 - 03:00 GMT - Vandenberg SLC5. Scout X-4 S123R Explorer 22 Mass: 52 kg (114 lb). Spacecraft: Beacon. Agency: NASA GSF. Perigee: 872 km (541 mi). Apogee: 1,053 km (654 mi). Inclination: 79.70 deg. Period: 104.30 min. Ionospheric and geodetic data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space.

1964 November 6 - 12:02 GMT - Wallops Island LA3. Scout X-4 S133R Explorer 23 Mass: 134 kg (295 lb). Spacecraft: S-55. Agency: NASA LaR. Perigee: 463 km (287 mi). Apogee: 980 km (600 mi). Inclination: 51.90 deg. Period: 99.20 min. Micrometeoroid data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1964 November 21 - 17:09 GMT - Vandenberg SLC5. Scout X-4 S135R Explorer 24 Mass: 9.00 kg (19.80 lb). Spacecraft: ADE. Agency: NASA LaR. Perigee: 530 km (320 mi). Apogee: 2,498 km (1,552 mi). Inclination: 81.40 deg. Period: 116.30 min. 12 foot dia. balloon; atmospheric density studies. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1964 December 15 - 20:20 GMT - Wallops Island LA3A. Scout X-4 S137R San Marco 1 Mass: 254 kg (559 lb). Spacecraft: San Marco. Agency: CRS. Perigee: 200 km (120 mi). Apogee: 842 km (523 mi). Inclination: 37.80 deg. Period: 95.10 min. Atmospheric density studies. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1964 December 22 - 04:00 GMT - Vandenberg LC-A. Blue Scout Jr 21-3 FAILURE: Third stage cut off early. Ion Engine Test C Technology mission Agency: USAF. Apogee: 500 km (310 mi). In this test, an additional wire neutralizer was incorporated and was immersed in the ion beam to provide a higher probability of adequate neutralization. The contact ion engine only achieved about 20% of full-thrust before reentry into the atmosphere. The short test time was due to a very short burn of the Scout vehicle's third stage. The high voltage was applied to the engine 7 minutes into the flight when the altitude was 490 km. Engine operation ended after 4 minutes when the altitude was only 80 km.

1965 January 28 - 12:51 GMT - Cape Canaveral LC18A. Blue Scout Jr 22-3 FAILURE: Failure. OAR 22-3 / AFCRL-309 Magnetosphere mission Agency: USAF. Apogee: 200 km (120 mi).

1965 March 30 - Cape Canaveral LC18A. Blue Scout Jr 22-4 OAR 22-4 / AFCRL-35 Magnetosphere mission Agency: USAF. Apogee: 12,067 km (7,498 mi).

1965 April 9 - 18:10 GMT - Cape Canaveral LC18A. Blue Scout Jr 22-9 OAR 22-9 / AFWL-14 Magnetosphere mission Agency: USAF. Apogee: 25,422 km (15,796 mi).

1965 April 29 - 14:17 GMT - Wallops Island LA3A. Scout X-4 S136R Explorer 27 Mass: 60 kg (132 lb). Spacecraft: Beacon. Agency: NASA GSF. Perigee: 932 km (579 mi). Apogee: 1,309 km (813 mi). Inclination: 41.20 deg. Period: 107.70 min. Battery failed in 1968; ionospheric research and geodetic data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space.

1965 May 12 - 16:00 GMT - Cape Canaveral LC18A. Blue Scout Jr 22-8 OAR 22-8 / AFCRL-335 Magnetosphere mission Agency: USAF. Apogee: 13,586 km (8,441 mi).

1965 June 9 - Cape Canaveral LC18A. Blue Scout Jr 22-5 OAR 22-5 / AFWL-304 Magnetosphere mission Agency: USAF. Apogee: 17,533 km (10,894 mi).

1965 August 10 - 17:54 GMT - Wallops Island LA3A. Scout B S131R SECOR 5 (EGRS 5) Mass: 24 kg (52 lb). Spacecraft: SECOR. Agency: NASA LaR. Perigee: 1,134 km (704 mi). Apogee: 2,419 km (1,503 mi). Inclination: 69.20 deg. Period: 122.20 min. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1965 November 19 - 04:48 GMT - Wallops Island LA3A. Scout X-4 S138R Explorer 30 Mass: 57 kg (125 lb). Spacecraft: IQSY. Agency: NRL. Perigee: 671 km (416 mi). Apogee: 856 km (531 mi). Inclination: 59.70 deg. Period: 100.10 min. Solar radiation data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1965 December 6 - 21:05 GMT - Vandenberg SLC5. Scout X-4 S139R FRANCE 1 Mass: 60 kg (132 lb). Spacecraft: FRANCE. Agency: CNES. Perigee: 696 km (432 mi). Apogee: 707 km (439 mi). Inclination: 75.90 deg. Period: 98.80 min. VLF wave propagation studies. Investigation of the properties of the ionized layers of the atmosphere by observation of the propagation of the properties of very low frequency waves in the ionosphere. First registered by the United States in A/AC.105/INF.125. Orbit given there was 99 .9 min, 749 x 753 km x 75.9 deg, with note: France provided the payload for 1965-101A.

1965 December 22 - 04:33 GMT - Vandenberg SLC5. Scout A S140C Transit O-6 Mass: 60 kg (132 lb). Spacecraft: Transit. Agency: USN. Perigee: 891 km (553 mi). Apogee: 1,059 km (658 mi). Inclination: 89.10 deg. Period: 104.60 min. Spacecraft built by Naval Avionics Facility, but refurbished by APL. Operated for 7 to 11 months, but then failed due to poor workmanship of NAFI components.

1966 January 28 - 17:06 GMT - Vandenberg SLC5. Scout A S142C Transit O-7 Mass: 50 kg (110 lb). Spacecraft: Transit. Agency: USN. Perigee: 850 km (520 mi). Apogee: 1,180 km (730 mi). Inclination: 90.00 deg. Period: 105.40 min. Naval Avionics Facility-assembled production spacecraft. Failed after a few weeks operation.

1966 February 10 - 00:55 GMT - Wallops Island LA3A. Scout X-4A S141C Reentry 4B Re-entry vehicle test Agency: NASA. Apogee: 175 km (108 mi).

1966 March 26 - 03:31 GMT - Vandenberg SLC5. Scout A S143C Transit O-8 Mass: 50 kg (110 lb). Spacecraft: Transit. Agency: USN. Perigee: 879 km (546 mi). Apogee: 1,099 km (682 mi). Inclination: 89.70 deg. Period: 104.90 min. Spacecraft built by Naval Avionics Facility, but refurbished by APL. Operated for 7 to 11 months, but then failed due to poor workmanship of NAFI components.

1966 April 22 - 09:45 GMT - Vandenberg SLC5. Scout B S145C OV3-01 Mass: 69 kg (152 lb). Spacecraft: OV3. Agency: USAF OAR. Perigee: 341 km (211 mi). Apogee: 3,585 km (2,227 mi). Inclination: 82.40 deg. Period: 126.40 min. Radiation data. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

1966 May 19 - 02:27 GMT - Vandenberg SLC5. Scout A S146C Transit O-9 Mass: 50 kg (110 lb). Spacecraft: Transit. Agency: USN. Perigee: 833 km (517 mi). Apogee: 951 km (590 mi). Inclination: 90.10 deg. Period: 102.80 min. Spacecraft built by Naval Avionics Facility, but refurbished by APL. Operated for 7 to 11 months, but then failed due to poor workmanship of NAFI components.

1966 June 10 - 04:15 GMT - Wallops Island LA3A. Scout B S147C OV3-04 Mass: 79 kg (174 lb). Spacecraft: OV3. Agency: USAF OAR. Perigee: 643 km (399 mi). Apogee: 4,704 km (2,922 mi). Inclination: 40.90 deg. Period: 142.90 min. Radiation measurements. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

1966 August 4 - 10:45 GMT - Vandenberg SLC5. Scout B S148C OV3-03 Mass: 75 kg (165 lb). Spacecraft: OV3. Agency: USAF OAR. Perigee: 349 km (216 mi). Apogee: 3,141 km (1,951 mi). Inclination: 81.40 deg. Period: 121.40 min. Radiation measurements. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

1966 August 18 - 02:25 GMT - Vandenberg SLC5. Scout A S149C Transit O-10 Mass: 58 kg (127 lb). Spacecraft: Transit. Agency: USN. Perigee: 1,038 km (644 mi). Apogee: 1,089 km (676 mi). Inclination: 88.90 deg. Period: 106.50 min. Spacecraft built by Naval Avionics Facility, but refurbished by APL. Only partially operational due to a decrease in the number of solar cells available for charging the batteries after thermal working of the solar cell interconnections in day/night cycles.

1966 October 28 - 11:56 GMT - Vandenberg SLC5. Scout B S150C OV3-02 Mass: 82 kg (180 lb). Spacecraft: OV3. Agency: USAF OAR. Perigee: 319 km (198 mi). Apogee: 1,599 km (993 mi). Inclination: 81.90 deg. Period: 104.20 min. Radiation data. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

1967 January 31 - 12:45 GMT - Vandenberg SLC5. Scout B S151C FAILURE: Failure. OV3-05 Spacecraft: OV3. Agency: AFSC.

1967 April 14 - 03:25 GMT - Vandenberg SLC5. Scout A S154C Transit O-12 Mass: 60 kg (132 lb). Spacecraft: Transit. Agency: USN. Perigee: 1,037 km (644 mi). Apogee: 1,064 km (661 mi). Inclination: 90.10 deg. Period: 106.20 min. First APL-built Transit Operational satellite. Operational life of this and subsequent Transits was over 14 years.

1967 April 26 - 10:06 GMT - San Marco -. Scout B S153C San Marco 2 Mass: 129 kg (284 lb). Spacecraft: San Marco. Agency: CRS. Perigee: 219 km (136 mi). Apogee: 741 km (460 mi). Inclination: 2.90 deg. Period: 94.20 min. Atmospheric density data. Scientific satellite launched from a mobile range off Formosa Bay (Kenya).

1967 May 5 - 16:00 GMT - Vandenberg SLC5. Scout A S155C Ariel 3 Mass: 90 kg (198 lb). Spacecraft: Ariel. Agency: UK SRC. Perigee: 499 km (310 mi). Apogee: 604 km (375 mi). Inclination: 80.60 deg. Period: 95.60 min. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1967 May 18 - 09:05 GMT - Vandenberg SLC5. Scout A S156C Transit O-13 Mass: 60 kg (132 lb). Spacecraft: Transit. Agency: USN. Perigee: 1,059 km (658 mi). Apogee: 1,088 km (676 mi). Inclination: 89.60 deg. Period: 106.70 min. Operational life over 20 years.

1967 May 30 - 02:06 GMT - Vandenberg SLC5. Scout B S152C FAILURE: Third stage failure. ESRO 2A Mass: 74 kg (163 lb). Spacecraft: ESRO. Agency: ESRO.

1967 September 25 - 08:25 GMT - Vandenberg SLC5. Scout A S157C Transit O-14 Mass: 60 kg (132 lb). Spacecraft: Transit. Agency