Sergeant

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Short range ballistic missile. IOC: 1962. Country: USA. Status: Retired 1994. Department of Defence Designation: MGM-29A. Popular Name: Sergeant. Alternate Designation: SSM-A-26 / M15.

Single-stage solid-propulsion tactical ballistic missile developed for the US Army. Surplus rockets and the Sergeant's rocket motor (known commercially as Castor) became the basis for many sounding rockets.

Historical Essay © Andreas Parsch

JPL/Sperry SSM-A-27/M15/MGM-29 Sergeant

The Sergeant was the first solid-fuel surface-to-surface missile deployed by the U.S. Army, and replaced the MGM-5 Corporal as the Army's medium-range tactical ballistic missile.

As early as 1948, JPL (Jet Propulsion Laboratory) and Thiokol studied new solid-propellant rocket designs for the U.S. Army under the name Sergeant, but this didn't produce an acceptable motor for tactical missile applications. However, solid-rocket development continued for General Electric's XSSM-A-13 Hermes A2 project, and a new motor with an internal "Burning Star" design was tested in the RV-A-10 test vehicles. This was a core-burning solid-fueled rocket engine, in which the surface area of the burning fuel remained constant. Therefore this engine type combined the advantages of the earlier end-burning (constant thrust) and core-burning (light-weight structure, because fuel acted as insulator) rocket designs. In late 1953 the RV-A-10 test program was completed, but the SSM-A-13 Hermes A2 had been cancelled. At the same time, the Army requested proposals from several companies for the development of a new solid-rocket SSM, to be named Sergeant. The Sergeant tactical surface-to-surface missile program was finally officially started in January 1955 with JPL as prime contractor, and the designation SSM-A-27 was assigned to the missile. Some sources show a designation of SSM-A-26, but this is definitely incorrect. The SSM-A-27 designator was short-lived anyway, because the U.S. Army stopped to use this designation system in June 1955.

The first experimental Sergeant missile was launched in 1956, and the Sperry Utah Company was chosen as primary subcontractor for missile production. In 1960, Sperry became prime contractor for the Sergeant, and in July 1962 the Sergeant was operationally deployed for the first time. By that time, the missile had received the designation Guided Missile, Artillery XM15, and quickly began to replace all MGM-5 Corporal missiles.

Compared to the Corporal, the Sergeant was a much better operational missile. Its solid-fuel rocket motor was safer and more reliable than the Corporal's liqued-fueled one. The guidance method was also different. Instead of command guidance, the Sergeant used an AN/DJW-8 inertial guidance system by Sperry Gyroscope. This was more resistant to countermeasures and required much less ground equipment. Because the solid-rocket motor could not be shut off once ignited, range was controlled by drag-brakes, which were opened by the guidance system about halfway through the planned flight path. These drag-brakes neutralized engine thrust, causing the missile to follow a ballistic flight path back to the ground. A complete Sergeant system could be moved with significantly less effort than a Corporal system, and the first missile launch could be achieved less than 90 minutes after the launch site had been reached (compared to 9 hours for Corporal).

In 1963 the XM15 Sergeant missile was designated as XMGM-29A, which was soon changed to MGM-29A. In 1972 the new MGM-52 Lance missile began to replace the MGM-29A, and the last Sergeant was retired from U.S. Army service in May 1977. In German Army service, the Sergeant lasted two years longer, until it was also replaced by the Lance. About 500 MGM-29 missiles were produced for the U.S. Army.

Specifications

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

Data for MGM-29A:

Length	10.5 m (34 ft 6 in)
Finspan	1.5 m (5 ft)
Diameter	0.78 m (31 in)
Weight	4570 kg (10100 lb)
Speed	Supersonic
Range	Min: 46 km (25 nm); Max: 140 km (75 nm)
Propulsion	Thiokol XM100 solid-fueled rocket motor; 200 kN (45000 lb) for 34 sec
Warhead	W-52 thermonuclear (200 kT)

Main Sources

[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
[3] Redstone Arsenal Historical Information Website

Manufacturer: JPL. Launches: 177. Failures: 3. Success Rate: 98.31%. First Launch Date: 1956-01-19. Last Launch Date: 1994-08-18. Launch data is: complete. Apogee: 80 km (49 mi). Liftoff Thrust: 200.000 kN (44,960 lbf). Total Mass: 4,530 kg (9,980 lb). Core Diameter: 0.79 m (2.59 ft). Total Length: 10.52 m (34.51 ft). Span: 1.80 m (5.90 ft). Standard warhead mass: 820 kg (1,800 lb). Maximum range: 139 km (86 mi). Number Standard Warheads: 1. Standard warhead: W52. Standard warhead yield: 200 KT. Boost Propulsion: Solid rocket. Guidance: Inertial. Maximum speed: 5,650 kph (3,510 mph). Development Cost $: 172.100 million. in: 1960 average dollars. Recurring Price $: 0.750 million. Total Number Built: 473. Total Development Built: 64. Total Production Built: 409. Flyaway Unit Cost $: 0.405 million. in: 1960 unit dollars. Version:

Sergeant Sounding Rocket. Sounding rocket.

Single stage vehicle consisting.

Apogee: 80 km (49 mi). Liftoff Thrust: 220.000 kN (49,450 lbf). Total Mass: 2,300 kg (5,000 lb). Core Diameter: 0.79 m (2.59 ft). Total Length: 5.10 m (16.70 ft).

Stage1: 1 x Sergeant. Gross Mass: 42 kg (92 lb). Empty Mass: 21 kg (46 lb). Motor: 1 x Sergeant. Thrust (vac): 6.660 kN (1,497 lbf). Isp: 235 sec. Burn time: 6.00 sec. Length: 1.00 m (3.20 ft). Diameter: 0.30 m (0.98 ft). Propellants: Solid.

Version:

Sergeant 5-stage. Test vehicle.

Five stage vehicle consisting of 1 x Sergeant + 1 x Lance + 1 x Lance + 1 x Recruit + 1 x T-55

Manufacturer: NASA. Launches: 4. Failures: 1. First Launch Date: 1958-06-27. Last Launch Date: 1960-03-24. Apogee: 35 km (21 mi). Liftoff Thrust: 230.000 kN (51,700 lbf). Core Diameter: 0.79 m (2.59 ft). Total Length: 14.00 m (45.00 ft).

Stage1: 1 x Sergeant. Gross Mass: 42 kg (92 lb). Empty Mass: 21 kg (46 lb). Motor: 1 x Sergeant. Thrust (vac): 6.660 kN (1,497 lbf). Isp: 235 sec. Burn time: 6.00 sec. Length: 1.00 m (3.20 ft). Diameter: 0.30 m (0.98 ft). Propellants: Solid.

Stage2: 1 x Castor Lance-2. Gross Mass: 800 kg (1,760 lb). Empty Mass: 274 kg (604 lb). Motor: 1 x TX-77. Thrust (vac): 227.000 kN (51,031 lbf). Burn time: 8.70 sec. Length: 4.60 m (15.00 ft). Diameter: 0.38 m (1.24 ft). Propellants: Solid.

Stage3: 1 x Castor Lance-2. Gross Mass: 800 kg (1,760 lb). Empty Mass: 274 kg (604 lb). Motor: 1 x TX-77. Thrust (vac): 227.000 kN (51,031 lbf). Burn time: 8.70 sec. Length: 4.60 m (15.00 ft). Diameter: 0.38 m (1.24 ft). Propellants: Solid.

Stage4: 1 x Journeyman-0. Gross Mass: 200 kg (440 lb). Motor: 1 x 1.5KS35000. Thrust (vac): 156.000 kN (35,070 lbf). Burn time: 1.50 sec. Length: 2.60 m (8.50 ft). Diameter: 0.23 m (0.75 ft). Propellants: Solid.

Stage5: 1 x HJ Nike Nike Recruit T55-5. Empty Mass: 12 kg (26 lb). Motor: 1 x T-55. Thrust (vac): 21.000 kN (4,720 lbf). Burn time: 1.30 sec. Length: 1.50 m (4.90 ft). Diameter: 0.15 m (0.49 ft). Propellants: Solid.

Version:

Shotput.
Shotput
Test vehicle.

Three stage vehicle consisting of 2 x Recruit + 1 x Sergeant + 1 x Altair

Manufacturer: NASA Langley. Launches: 7. First Launch Date: 1959-10-28. Last Launch Date: 1963-08-02. Apogee: 400 km (240 mi). Liftoff Thrust: 220.000 kN (49,450 lbf). Total Mass: 5,100 kg (11,200 lb). Core Diameter: 0.79 m (2.59 ft). Total Length: 9.90 m (32.40 ft).

Stage0: 2 x Journeyman-0. Gross Mass: 200 kg (440 lb). Motor: 1 x 1.5KS35000. Thrust (vac): 156.000 kN (35,070 lbf). Burn time: 1.50 sec. Length: 2.60 m (8.50 ft). Diameter: 0.23 m (0.75 ft). Propellants: Solid.

Stage1: 1 x Little Joe 1 2P-1. Gross Mass: 4,200 kg (9,200 lb). Motor: 1 x Pollux. Burn time: 38 sec. Length: 5.70 m (18.70 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.

Stage2: 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.

Version:

Castor-Recruit. Sounding rocket.

Two stage vehicle consisting of 1 x Castor + 1 x Recruit

Launches: 1. First Launch Date: 1962-10-20. Last Launch Date: 1962-10-20. Apogee: 150 km (90 mi). Liftoff Thrust: 0 N ( lbf). Core Diameter: 0.79 m (2.59 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 Journeyman-0. Gross Mass: 200 kg (440 lb). Motor: 1 x 1.5KS35000. Thrust (vac): 156.000 kN (35,070 lbf). Burn time: 1.50 sec. Length: 2.60 m (8.50 ft). Diameter: 0.23 m (0.75 ft). Propellants: Solid.

Version:

Castor. Suborbital launch vehicle.

Single stage version.

Launches: 8. First Launch Date: 1967-01-11. Last Launch Date: 1978-12-05. Apogee: 300 km (180 mi). Liftoff Thrust: 235.000 kN (52,830 lbf). Total Mass: 5,200 kg (11,400 lb). Core Diameter: 0.79 m (2.59 ft). Total Length: 8.00 m (26.20 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.

Version:

Castor Lance. Sounding rocket.

Two stage vehicle consisting of 1 x Castor + 1 x Lance

Launches: 2. Failures: 1. First Launch Date: 1973-05-25. Last Launch Date: 1985-06-17. Apogee: 600 km (370 mi). Liftoff Thrust: 0 N ( lbf). Core Diameter: 0.79 m (2.59 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 Castor Lance-2. Gross Mass: 800 kg (1,760 lb). Empty Mass: 274 kg (604 lb). Motor: 1 x TX-77. Thrust (vac): 227.000 kN (51,031 lbf). Burn time: 8.70 sec. Length: 4.60 m (15.00 ft). Diameter: 0.38 m (1.24 ft). Propellants: Solid.

Version:

Sergeant Hydac. Sounding rocket.

Two stage vehicle consisting of 1 x Sergeant + 1 x Hydac

Manufacturer: Aerojet. Launches: 7. First Launch Date: 1974-12-18. Last Launch Date: 1981-03-12. Apogee: 500 km (310 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 4,800 kg (10,500 lb). Core Diameter: 0.79 m (2.59 ft). Total Length: 13.80 m (45.20 ft).

Stage1: 1 x Sergeant. Gross Mass: 42 kg (92 lb). Empty Mass: 21 kg (46 lb). Motor: 1 x Sergeant. Thrust (vac): 6.660 kN (1,497 lbf). Isp: 235 sec. Burn time: 6.00 sec. Length: 1.00 m (3.20 ft). Diameter: 0.30 m (0.98 ft). Propellants: Solid.

Stage2: 1 x Talos Sergeant Hydac-3. Gross Mass: 300 kg (660 lb). Motor: 1 x Hydac. Thrust (vac): 58.700 kN (13,196 lbf). Length: 3.70 m (12.10 ft). Diameter: 0.23 m (0.75 ft). Propellants: Solid.

Sergeant Chronology

1956 January 19 - White Sands -. LV Model: Sounding Rocket . Sergeant 1 Test mission Agency: USA. Apogee: 50 km (31 mi).

1956 February 28 - White Sands -. LV Model: Sounding Rocket . Sergeant 2 Test mission Agency: USA. Apogee: 50 km (31 mi).

1956 April 24 - White Sands -. LV Model: Sounding Rocket . Sergeant 3 Test mission Agency: USA. Apogee: 50 km (31 mi).

1956 November 3 - White Sands -. LV Model: Sounding Rocket . Sergeant 4 Test mission Agency: USA. Apogee: 50 km (31 mi).

1957 January 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1957 April 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1957 October 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1957 November 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1958 January 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1958 March 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1958 May 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1958 June 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1958 June 27 - Wallops Island -. Mercury-type Re-entry Vehicle test Agency: NACA. Apogee: 34 km (21 mi).

1958 August 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1958 October 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1958 November 20 - Wallops Island -. FAILURE: Failure. Mercury-type Re-entry Vehicle test Agency: NACA. Apogee: 30 km (18 mi).

1958 December 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1959 March 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1959 August 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1959 October 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1959 October 28 - 22:40 GMT - Wallops Island -. Shotput 1 E60 Echo spacecraft test Agency: NASA LaRC. Apogee: 400 km (240 mi).

1960 January 8 - Wallops Island -. Mercury model Re-entry vehicle test Agency: NASA. Apogee: 34 km (21 mi).

1960 January 16 - 22:35 GMT - Wallops Island -. Shotput 2 E60 Echo spacecraft test Agency: NASA LaRC. Apogee: 413 km (256 mi).

1960 February 27 - 23:20 GMT - Wallops Island -. Shotput 3 E60 Echo spacecraft test Agency: NASA LaRC. Apogee: 400 km (240 mi).

1960 March 24 - Wallops Island -. Mercury model Re-entry vehicle test Agency: NASA. Apogee: 34 km (21 mi).

1960 April 1 - Wallops Island -. Shotput 4 E60 Echo spacecraft test Agency: NASA LaRC. Apogee: 400 km (240 mi).

1960 May 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1960 May 31 - Wallops Island -. Shotput 5 E60 Echo spacecraft test Agency: NASA LaRC. Apogee: 400 km (240 mi).

1960 July 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1960 August 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1960 September 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1960 December 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1961 January 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1961 March 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1961 May 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1961 September 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1962 July 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1962 September 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1962 October 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1962 October 20 - 08:30 GMT - Johnston Island -. CHECKMATE Nuclear test Agency: AEC. Apogee: 147 km (91 mi). Test of the Los Alamos XW-50X1 60 kiloton nuclear warhead. Launch vehicle was a solid propellant XM-33 Strypi rocket with a Recruit booster stage. The warhead detonated at an altitude of 147 km, 66 km from Johnston Island. Observers on the island saw a green and blue circular region surrounded by a red ring. This faded in less than a minute. Blue-green streamers and pink striations developed that lasted half an hour. At this yield, even with the high altitude, extensive disruption of communications were not reported.

1962 October 24 - White Sands -. Tactical Field Fir. Agency: USA. Apogee: 50 km (31 mi).

1962 November 2 - White Sands -. Tactical Field Fir. Agency: USA. Apogee: 50 km (31 mi).

1962 December 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1963 January 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1963 February 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1963 March 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1963 March 18 - San Nicolas -. Deployability test Agency: USA. Apogee: 50 km (31 mi).

1963 March 20 - San Nicolas -. Deployability test Agency: USA. Apogee: 50 km (31 mi).

1963 March 21 - San Nicolas -. Deployability test Agency: USA. Apogee: 50 km (31 mi).

1963 April 20 - Wallops Island -. Shotput 6 San Marco Satellite test Agency: NASA. Apogee: 426 km (264 mi).

1963 May 13 - Datil -. Off Range Test Agency: USA. Apogee: 50 km (31 mi).

1963 May 14 - Datil -. Off Range Test Agency: USA. Apogee: 50 km (31 mi).

1963 May 16 - Datil -. Off Range test Agency: USA. Apogee: 50 km (31 mi).

1963 June 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1963 August 2 - 21:43 GMT - Wallops Island -. Shotput 7 San Marco Satellite test Agency: NASA. Apogee: 294 km (182 mi).

1963 October 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1963 December 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1964 February 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1964 March 13 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1964 June 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1964 October 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1964 December 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1965 February 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1965 March 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1965 June 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1965 August 4 - White Sands -. SIGS Test Technology mission Agency: USN. Apogee: 10 km (6 mi).

1966 June 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1967 January 11 - Vandenberg 4300C. Marquardt Scramjet Technology mission Agency: USAF AFSC. Apogee: 54 km (33 mi).

1967 June 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1967 December 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1968 May 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1968 June 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1968 October 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1968 December 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1969 June 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1969 December 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1970 June 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1970 October 9 - Wallops Island LA4. Castor-2R SPED II re-entry vehicle test flight Agency: NASA. Apogee: 85 km (52 mi).

1970 December 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1971 May 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1971 November 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1971 December 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1972 June 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1972 November 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1973 May 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1973 May 25 - 15:20 GMT - Natal -. Castor Lance CRL A44.320-01 Infrared Radiometer Aeronomy infrared mission Agency: AFCRL. Apogee: 569 km (353 mi).

1973 November 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1974 May 1 - White Sands -. Agency: USA. Apogee: 50 km (31 mi).

1974 December 18 - 00:58 GMT - Poker Flat -. Sergeant Hydac SH74-1 Ballistic Test Agency: Sandia?. Apogee: 500 km (310 mi).

1975 January 9 - Kwajalein RN. Castor-2R Re-entry Vehicle test Agency: USAF. Apogee: 200 km (120 mi).

1975 March 12 - 07:48 GMT - Poker Flat -. Sergeant Hydac IC519.07-1B ICECAP 75A Auroral mission Agency: DNA/AFCRL. Apogee: 500 km (310 mi).

1975 April 13 - 09:46 GMT - Poker Flat -. Castor DNA EX531.43-1 EXCEDE Active plasma mission Agency: USAF. Apogee: 100 km (60 mi).

1975 June 13 - 00:19 GMT - Poker Flat -. LV Model: Sounding Rocket . Sergeant S75-1 FAILURE: Failure. PF-SGT-100 Ballistic test Agency: DNA. Apogee: 8.00 km (4.90 mi).

1975 August 7 - Kwajalein RN. Castor-2R Technology mission Agency: USAF. Apogee: 200 km (120 mi).

1975 October 30 - 23:52 GMT - Poker Flat -. LV Model: Sounding Rocket . Sergeant EX530.90-1/S75-2 PF-SGT-101 test Agency: DNA. Apogee: 100 km (60 mi).

1975 December 4 - Kwajalein RN. Castor-2R Technology mission Agency: USAF. Apogee: 200 km (120 mi).

1976 January 23 - 10:06 GMT - Poker Flat -. LV Model: Sounding Rocket . Sergeant WA630.50-1 Optical Track test Agency: DNA. Apogee: 80 km (49 mi).

1976 February 28 - 05:46 GMT - Poker Flat -. LV Model: Sounding Rocket . Sergeant EX630.42-1 EXCEDE SWIR Active plasma mission Agency: DNA/AFCRL. Apogee: 100 km (60 mi).

1976 April 1 - 08:05 GMT - Poker Flat -. LV Model: Sounding Rocket . Sergeant IC630.02-1A ICECAP 76 HIRIS Auroral mission Agency: DNA/AFCRL. Apogee: 130 km (80 mi).

1976 June 27 - Kwajalein RN. Castor-2R Technology mission Agency: USAF. Apogee: 200 km (120 mi).

1977 November 13 - 08:55 GMT - Poker Flat -. LV Model: Sounding Rocket . Sergeant DNA IC730.09-1 FWIF I Aeronomy / aurora / solar mission Agency: DNA. Apogee: 141 km (87 mi).

1978 February 28 - 08:10 GMT - Poker Flat -. Sergeant Hydac DNA IC819.08-1 MULTI-WIDEBAND Infrared technology mission Agency: DNA. Apogee: 458 km (284 mi).

1978 June 8 - 20:00 GMT - Poker Flat -. LV Model: Sounding Rocket . Sergeant EX830.56-1 Recovery test Agency: DNA. Apogee: 105 km (65 mi).

1978 November 13 - 12:44 GMT - Poker Flat -. LV Model: Sounding Rocket . Sergeant DNA IC830.09-1A FWIF II Auroral Infrared mission Agency: DNA. Apogee: 141 km (87 mi).

1978 December 5 - Kwajalein RN. Castor-2R DOT 1 Interceptor mission Agency: USAF. Apogee: 235 km (146 mi).

1979 September 25 - Barking Sands -. HAVE LENT IV ABRES test Agency: ABRES. Apogee: 400 km (240 mi).

1981 February 5 - 11:25 GMT - Poker Flat -. LV Model: Sounding Rocket . Sergeant GL A30.072 FWIF IV Auroral mission Agency: USAF GL. Apogee: 130 km (80 mi).

1981 February 25 - 17:20 GMT - Poker Flat -. HAVE SLED test Agency: USAF BMO. Apogee: 400 km (240 mi).

1981 March 5 - 16:48 GMT - Poker Flat -. HAVE SLED test Agency: USAF BMO. Apogee: 400 km (240 mi).

1981 March 12 - 04:30 GMT - Poker Flat -. HAVE SLED test Agency: USAF BMO. Apogee: 400 km (240 mi).

1981 November 7 - 12:03 GMT - Poker Flat -. LV Model: Sounding Rocket . Sergeant GL A30.175 FWIF V Auroral mission Agency: USAF GL. Apogee: 130 km (80 mi).

1983 April 13 - 09:06 GMT - Poker Flat -. LV Model: Sounding Rocket . Sergeant GL A30.276 FWIF VI Auroral mission Agency: USAF GL. Apogee: 140 km (80 mi).

1985 June 17 - 04:15 GMT - Natal -. Castor Lance GL A44.362 FAILURE: Failure. BEAM Infrared astronomy mission Agency: USAF GL. Apogee: 500 km (310 mi).

1994 July 8 - Wallops Island -. MSTI-2 Target Target mission Agency: BMDO. Apogee: 100 km (60 mi).

1994 August 8 - Wallops Island -. CEC Target Target mission Agency: USN. Apogee: 100 km (60 mi).

1994 August 18 - Wallops Island -. JTF-95 MSTI Target Target mission Agency: DoD. Apogee: 100 km (60 mi).

Bibliography:

McDowell, Jonathan, Jonathan's Space Home Page (launch records), Harvard University, 1997-present. Web Address when accessed: http://www.planet4589.org/jsr.html.
Parsch, Andreas, DesignationSystems.Net, Web Address when accessed: http://www.designation-systems.net/.

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