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Terrier Malemute
Surface-to-air missile. IOC: 1956. Country: USA. Status: Active. Department of Defence Designation: RIM-2. Popular Name: Terrier.

Standard US Navy surface-to-air missile develoed during the 1950's. Modified single stage Navy Terrier missiles were used as sounding rockets, sometimes supplemented with upper stages.

Historical Essay © Andreas Parsch

General Dynamics (Convair) SAM-N-7/RIM-2 Terrier

The Terrier was the U.S. Navy's first operational shipborne medium-range surface-to-air missile. It was one result of the Bumblebee program, whose ultimate goal was the development of the SAM-N-6 Talos long-range surface-to-air missile. During devolpment of Talos, a Supersonic Test Vehicle (STV, CTV-N-8) was built to evaluate the guidance system at supersonic speeds. Because the results were promising, and the development of the complicated Talos would take many more years, it was decided to develop the STV into a tactical missile, the Terrier. The flight tests of the Terrier began in 1951, when the designation SAM-N-7 was also assigned. It took a few years to get the bugs out of the system, and the Terrier was not operational until 1956.

Production started with the SAM-N-7, but after a few rounds switched to the slightly reengineered SAM-N-7a Terrier 1a, soon to be known as Terrier BW-0 (Beam-riding, Wing-controlled, series 0). It employed a beam-riding guidance system, and used wings for flight control. It was powered by an Allegany Ballistics solid-fuel booster and an MW Kellogg solid-fuel sustainer motor. Terrier 1b was to be a version with repackaged electronics (designed by APL/Philco), but this was not produced. Another electronics redesign effort (initiated by BuOrd, designed by Motorola) resulted in the SAM-N-7c Terrier 1c version. This variant, later known as Terrier BW-1, had essentially the same characteristics as the BW-0, but was easier to produce and had higher reliability. The BW-0/1 versions were effective only against subsonic targets at altitudes up to 12 km (40000 ft).

The usage of suffix letters for the basic SAM-N-7 designation to distinguish between Terrier variants was short-lived, and was discontinued during the production of the BW-1. The Terrier was henceforth simply known as SAM-N-7 (and even that was rarely used), and the variants were designated by the suffixes BW-0, BW-1 (and others, which see below).

The next version of the Terrier was the BT-3 (Beam-riding, Tail-controlled, series 3; series 2 was reserved for a motor improvement, which was not built). This missile had a new airframe, where the wings were replaced by fixed strakes, and the control surfaces were moved to the tail. The tail-control significantly enhanced the missile's agility. The BT-3 also had an improved autopilot and a new propulsion system (with a new sustainer, and an additional auxiliary solid-fuel power system) for higher speed and range. The first successful test was accomplished in 1954, and the BT-3 was operational in 1956. The improvements made the BT-3 effective against supersonic targets.

An improved version, called Terrier BT-3A, had a longer-burning charge for the auxiliary power system, and an end-burning sustainer, which doubled the missile range to about 37 km (20 nm). The BT-3A was also the first Terrier which could be used effectively in a surface-to-surface (anti-ship) mode. The BT-3A(N) was a nuclear armed BT-3A (the only nuclear Terrier version), which had a 1 kT W-45-0 warhead.

The next development step was to change the beam-riding guidance to semi-active radar homing. The Terrier HT-3 used many components of the RIM-24 Tartar missile, which was itself essentially a short-range Terrier without booster. In 1957, the radar homing system for Terrier was tested with a converted wing-controlled missile, designated XHW-1. The production HT-3 used a C-band radar seeker. The SARH guidance greatly increased the effectiveness of the missile against low-flying targets.

In 1963, all variants of Terrier were redesignated in the RIM-2 series, as follows:

Old Designation New Designation
SAM-N-7 BW-0 RIM-2A
SAM-N-7 BW-1 RIM-2B
SAM-N-7 BT-3 RIM-2C
SAM-N-7 BT-3A/-3A(N) RIM-2D
SAM-N-7 HT-3 RIM-2E

As can be seen from this table, the old SAM-N-7 series designations did not use any suffix letters to designate variants.

The last Terrier variant was the RIM-2F, an improved RIM-2E. It had a new sustainer motor and power supply, which again doubled the missile's range, to about 75 km (40 nm). The RIM-2F was also known as HTR-3 (Homing Terrier, Retrofit). Additional improvements included solid-state electronics, improved ECCM, multiple-target ability, and improved anti-ship capability. Many RIM-2E missiles were brought up to RIM-2F standard.

Prodcution of the RIM-2 Terrier ended in 1966, after approximately 8000 missiles had been built. The RIM-2F was gradually replaced by the RIM-67 Standard ER missile, and the last Terriers were retired at the end of the 1980's. Currently Raytheon is converting old Terrier rounds to TMT (Terrier Missile Target) configuration, which can be used as sea-skimming or ballistic targets. The targets are upgraded with Standard missile components, and are possibly designated RQM-67A.

Specifications

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

Data for RIM-2B/D/F:

  RIM-2B RIM-2D/F
Length (incl. booster) 8.25 m (27 ft 1 in) 8.0 m (26 ft 4 in)
Wingspan 1.20 m (47.3 in) 0.61 m (24 in)
Finspan 1.03 m (40.5 in) 1.07 m (42.3 in)
Diameter 0.34 m (13.5 in)
Weight (w/o booster) 480 kg (1060 lb); booster: 584 kg (1290 lb) 535 kg (1180 lb); booster: 825 kg (1820 lb)
Speed Mach 1.8 Mach 3.0
Ceiling 12200 m (40000 ft) 24400 m (80000 ft)
Range 19 km (10 nm) RIM-2D: 37 km (20 nm); RIM-2F: 75 km (40 nm)
Propulsion Solid-fueled rocket booster
Solid-fueled rocket sustainer
Warhead 100 kg (218 lb) controlled-fragmentation warhead; RIM-2D (BT-3A(N)): W-45-0 nuclear warhead (1 kT)
Main Sources

[1] Norman Friedman: "US Naval Weapons", Conway Maritime Press, 1983
[2] Bill Gunston: "The Illustrated Encyclopedia of Rockets and Missiles", Salamander Books Ltd, 1979
[3] James N. Gibson: "Nuclear Weapons of the United States", Schiffer Publishing Ltd, 1996


Manufacturer: Convair. Launches: 156. Failures: 15. Success Rate: 90.38%. First Launch Date: 1959-05-01. Last Launch Date: 2007-12-17. Launch data is: continuing. Apogee: 30 km (18 mi). Liftoff Thrust: 22.500 kN (5,058 lbf). Total Mass: 1,392 kg (3,068 lb). Core Diameter: 0.34 m (1.11 ft). Total Length: 8.08 m (26.50 ft). Span: 1.59 m (5.21 ft). Standard warhead mass: 110 kg (240 lb). Maximum range: 37 km (22 mi). Number Standard Warheads: 1. Standard warhead: W45. Standard warhead yield: 1.00 KT. Boost Propulsion: Solid rocket. Guidance: Beam rider + Command Link. Maximum speed: 3,270 kph (2,030 mph). Ceiling: 15,200 m (49,800 ft). Floor: 15 m (49 ft). Surveillance Radar: SPQ-5/C. Tracking Radar: SPG-49. Total Number Built: 3000. Flyaway Unit Cost $: 0.062 million. in: 1959 unit dollars.

  • Stage1: 1 x Black Brant X-1. Gross Mass: 900 kg (1,980 lb). Empty Mass: 322 kg (709 lb). Motor: 1 x X-256. Thrust (vac): 257.500 kN (57,888 lbf). Burn time: 4.40 sec. Length: 3.90 m (12.70 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.
Version:

Land-Based Version.

Land based-version of Terrier surface-to-air missile. Development begun in 1951. Project cancelled in 1956.

Development Cost $: 18.600 million. in: 1954 average dollars. Version:

RIM-2A. Department of Defence Designation: RIM-2A. Popular Name: Terrier BW-0. Alternate Designation: SAM-N-7.

Version:

RIM-2B. Department of Defence Designation: RIM-2B. Popular Name: Terrier BW-1. Alternate Designation: SAM-N-7.

Version:

RIM-2C. Department of Defence Designation: RIM-2C. Popular Name: Terrier BT-3.

Version:

RIM-2D. Department of Defence Designation: RIM-2D. Popular Name: Terrier BT-3A.

Nuclear warhead.

Standard warhead mass: 166 kg (365 lb). Standard warhead: W45 Mod 1. Standard warhead yield: 1.00 KT. Version:

RIM-2F. Department of Defence Designation: RIM-2F. Popular Name: Terrier HT-3.

Version:

Terrier Asp. Sounding rocket. Status: Retired 1959.

Two stage vehicle consisting of 1 x Terrier + 1 x Asp

Launches: 1. First Launch Date: 1959-09-30. Last Launch Date: 1959-09-30. Apogee: 100 km (60 mi). Liftoff Thrust: 258.000 kN (58,000 lbf). Total Mass: 1,100 kg (2,400 lb). Core Diameter: 0.46 m (1.50 ft). Total Length: 10.00 m (32.00 ft).

  • Stage1: 1 x Black Brant X-1. Gross Mass: 900 kg (1,980 lb). Empty Mass: 322 kg (709 lb). Motor: 1 x X-256. Thrust (vac): 257.500 kN (57,888 lbf). Burn time: 4.40 sec. Length: 3.90 m (12.70 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.
  • Stage2: 1 x Asp. Gross Mass: 100 kg (220 lb). Empty Mass: 18 kg (39 lb). Motor: 1 x RM-1100. Thrust (vac): 26.000 kN (5,845 lbf). Burn time: 5.30 sec. Length: 2.70 m (8.80 ft). Diameter: 0.17 m (0.54 ft). Propellants: Solid.
Version:

Terrier ASROC Cajun. Sounding rocket. Status: Retired 1959.

Three stage vehicle consisting of 1 x Terrier + 1 x ASROC + 1 x Cajun

Launches: 3. Failures: 2. First Launch Date: 1959-05-01. Last Launch Date: 1959-08-12. Apogee: 100 km (60 mi). Liftoff Thrust: 258.000 kN (58,000 lbf). Total Mass: 1,400 kg (3,000 lb). Core Diameter: 0.46 m (1.50 ft). Total Length: 11.00 m (36.00 ft).

  • Stage1: 1 x Black Brant X-1. Gross Mass: 900 kg (1,980 lb). Empty Mass: 322 kg (709 lb). Motor: 1 x X-256. Thrust (vac): 257.500 kN (57,888 lbf). Burn time: 4.40 sec. Length: 3.90 m (12.70 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.
  • Stage2: 1 x Terrier ASROC Cajun-2. Gross Mass: 400 kg (880 lb). Empty Mass: 40 kg (88 lb). Motor: 1 x ASROC. Length: 4.50 m (14.70 ft). Diameter: 0.34 m (1.11 ft). Propellants: Solid.
  • Stage3: 1 x Cajun Dart-1. Gross Mass: 100 kg (220 lb). Empty Mass: 22 kg (48 lb). Motor: 1 x Cajun. Thrust (vac): 36.000 kN (8,093 lbf). Burn time: 3.00 sec. Length: 2.60 m (8.50 ft). Diameter: 0.17 m (0.55 ft). Propellants: Solid.
Version:

Terrier Asp IV. Sounding rocket. Status: Retired 1962.

Two stage vehicle consisting of 1 x Terrier + 1 x Asp IV

Launches: 2. First Launch Date: 1962-03-14. Last Launch Date: 1962-12-13. Apogee: 100 km (60 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 1,100 kg (2,400 lb). Core Diameter: 0.46 m (1.50 ft). Total Length: 10.00 m (32.00 ft).

  • Stage1: 1 x Black Brant X-1. Gross Mass: 900 kg (1,980 lb). Empty Mass: 322 kg (709 lb). Motor: 1 x X-256. Thrust (vac): 257.500 kN (57,888 lbf). Burn time: 4.40 sec. Length: 3.90 m (12.70 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.
  • Stage2: 1 x Asp IV. Gross Mass: 94 kg (207 lb). Empty Mass: 27 kg (59 lb). Motor: 1 x RM-1400. Thrust (vac): 12.700 kN (2,855 lbf). Burn time: 12 sec. Length: 2.80 m (9.10 ft). Diameter: 0.17 m (0.54 ft). Propellants: Solid.
Version:

Terrier/551. Sounding rocket. Status: Retired 1966.

Two stage vehicle consisting of 1 x Terrier + 1 x NOTS 551

Manufacturer: NOTS. Launches: 2. Failures: 1. First Launch Date: 1965-10-20. Last Launch Date: 1966-08-02. Apogee: 450 km (270 mi). Liftoff Thrust: 258.000 kN (58,000 lbf). Total Mass: 1,300 kg (2,800 lb). Core Diameter: 0.46 m (1.50 ft). Total Length: 8.40 m (27.50 ft).

  • Stage1: 1 x Black Brant X-1. Gross Mass: 900 kg (1,980 lb). Empty Mass: 322 kg (709 lb). Motor: 1 x X-256. Thrust (vac): 257.500 kN (57,888 lbf). Burn time: 4.40 sec. Length: 3.90 m (12.70 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.
  • Stage2: 1 x Terrier/551-2. Gross Mass: 400 kg (880 lb). Empty Mass: 85 kg (187 lb). Motor: 1 x NOTS Mod 551-B. Burn time: 28 sec. Length: 3.00 m (9.80 ft). Diameter: 0.34 m (1.11 ft). Propellants: Solid.
Version:

Terrier Hydac. Sounding rocket. Status: Retired 1966.

Manufacturer: Lockheed. Launches: 1. First Launch Date: 1966-03-01. Last Launch Date: 1966-03-01. Apogee: 500 km (310 mi). Liftoff Thrust: 0 N ( lbf). Core Diameter: 0.46 m (1.50 ft). Total Length: 10.00 m (32.00 ft).

  • Stage1: 1 x Black Brant X-1. Gross Mass: 900 kg (1,980 lb). Empty Mass: 322 kg (709 lb). Motor: 1 x X-256. Thrust (vac): 257.500 kN (57,888 lbf). Burn time: 4.40 sec. Length: 3.90 m (12.70 ft). Diameter: 0.46 m (1.50 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.
Version:

Terrier Malemute. Sounding rocket. Status: Active.

The Terrier-Malemute launch vehicle was a high performance two-stage vehicle used for payloads weighing less than 180 kg, generally used for relatively lightweight plasma physics payloads. Payload 90 kg to 650 km or 180 kg to 420 km.

The first stage booster consisted of a Terrier MK 12 Mod 1 rocket motor with four 0.5 square meter fin panels arranged in a cruciform configuration. The Terrier booster had an overall diameter of 46 cm. For a payload weight of 90 kg, the longitudinal acceleration during the boost phase was 26g's. The second stage propulsion unit was a Thiokol Malemute TU-758 rocket motor which was designed especially for high altitude research rocket applications. The external diameter of the Malemute was 41 cm.

The average thrust was 42.7 kN. The maximum thrust level was approximately 63.5 kN which resulted in a maximum longitudinal acceleration during second stage burning of 32g's for a 90 kg payload. Liftoff weight of the Terrier-Malemute launch vehicle, less payload, was approximately 1478 kg. This vehicle was usually rail launched and could be accommodated at most established launch ranges.

The Terrier-Malemute vehicle was particularly suited for lower weight payloads; performance dropped appreciably as payload weight increased. Bulbous diameter payloads could be accommodated on the Terrier-Malemute; however, the high dynamic pressures encountered by this vehicle resultedin high aerodynamic heating rates and high vehicle structural loads Thus, payload design characteristics had to be carefully considered.

Manufacturer: Sandia. Launches: 46. Failures: 5. Success Rate: 89.13%. First Launch Date: 1974-11-11. Last Launch Date: 2004-08-15. Apogee: 500 km (310 mi). Liftoff Thrust: 258.000 kN (58,000 lbf). Total Mass: 1,568 kg (3,456 lb). Core Diameter: 0.46 m (1.50 ft). Total Length: 12.70 m (41.60 ft).

  • Stage1: 1 x Black Brant X-1. Gross Mass: 900 kg (1,980 lb). Empty Mass: 322 kg (709 lb). Motor: 1 x X-256. Thrust (vac): 257.500 kN (57,888 lbf). Burn time: 4.40 sec. Length: 3.90 m (12.70 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.
  • Stage2: 1 x Terrier Malemute-2. Gross Mass: 600 kg (1,320 lb). Empty Mass: 100 kg (220 lb). Motor: 1 x TU-758. Thrust (vac): 55.100 kN (12,387 lbf). Burn time: 22 sec. Length: 3.30 m (10.80 ft). Diameter: 0.41 m (1.34 ft). Propellants: Solid.
Version:

Terrier Nike. Sounding rocket. Status: Retired 1974.

Manufacturer: Sandia. Launches: 1. First Launch Date: 1974-01-01. Last Launch Date: 1974-01-01. Apogee: 2.00 km (1.20 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 1,100 kg (2,400 lb). Core Diameter: 0.46 m (1.50 ft). Total Length: 9.80 m (32.10 ft).

  • Stage1: 1 x Black Brant X-1. Gross Mass: 900 kg (1,980 lb). Empty Mass: 322 kg (709 lb). Motor: 1 x X-256. Thrust (vac): 257.500 kN (57,888 lbf). Burn time: 4.40 sec. Length: 3.90 m (12.70 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.
  • Stage2: 1 x HJ Nike Nike-3. Gross Mass: 599 kg (1,320 lb). Empty Mass: 256 kg (564 lb). Motor: 1 x M5E1. Thrust (vac): 195.600 kN (43,973 lbf). Burn time: 3.40 sec. Length: 3.60 m (11.80 ft). Diameter: 0.42 m (1.37 ft). Propellants: Solid.
Version:

Terrier LEAP. Anti-ballistic missile. Status: Retired 1995.

Three stage vehicle consisting of 1 x Terrier Mk 70 + 1 x Mk 30 + 1 x ASAS

Launches: 4. First Launch Date: 1992-09-24. Last Launch Date: 1995-03-28. Apogee: 30 km (18 mi). Liftoff Thrust: 258.000 kN (58,000 lbf). Total Mass: 1,300 kg (2,800 lb). Core Diameter: 0.46 m (1.50 ft). Total Length: 10.00 m (32.00 ft).

  • Stage1: 1 x Terrier Mk 70 Oriole-1. Gross Mass: 1,038 kg (2,288 lb). Empty Mass: 290 kg (630 lb). Motor: 1 x TX-664-4. Burn time: 6.20 sec. Length: 3.94 m (12.92 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.
  • Stage2: 1 x SM-1ER-2. Gross Mass: 400 kg (880 lb). Motor: 1 x Mk 30. Length: 3.50 m (11.40 ft). Diameter: 0.35 m (1.14 ft). Propellants: Solid.
  • Stage3: 1 x SM-3-3. Gross Mass: 100 kg (220 lb). Motor: 1 x SM3 TSRM. Thrust (vac): 7.000 kN (1,574 lbf). Burn time: 15 sec. Length: 0.90 m (2.95 ft). Diameter: 0.33 m (1.08 ft). Propellants: Solid.
Version:

Terrier Improved Orion. Sounding rocket. Status: Active.

Two stage vehicle consisting of 1 x Terrier + 1 x Improved Orion

The Terrier-Orion rocket system was a two stage spin stabilized rocket system which utilized a Terrier MK 12 Mod 1 for the first stage and an Improved Orion motor for the second stage. The vehicle was typically configured with spin motors and the total weight of this configuration, excluding the payload, was approximately 1305 kg.

The Orion motor utilized a clamp-released/load-bearing tail can to interface with the Terrier motor. This was a rail-launched configuration that can be supported at most fixed and mobile launch ranges.

Payload configurations supported by this vehicle included 36 cm and bulbous 44 cm diameters. Payload weights ranging from 90 to 360 kg could achieve altitudes of approximately 200 to 80 kilometers respectively.

Available support systems include thed standard 36 cm Ignition Recovery Module Assembly (IRMA), ACS systems, and nose cones of various configurations. The complete cadre of 44 cm diameter support systems was available for use with the bulbous payloads. These included fixed and deployable nose cones; fine, course, rate control, and magnetic ACS systems; separation and despin systems; and forward and aft recovery systems.

Launches: 44. Failures: 3. Success Rate: 93.18%. First Launch Date: 1994-04-05. Last Launch Date: 2007-09-06. Apogee: 300 km (180 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 1,315 kg (2,899 lb). Core Diameter: 0.46 m (1.50 ft). Total Length: 12.80 m (41.90 ft).

  • Stage1: 1 x Black Brant X-1. Gross Mass: 900 kg (1,980 lb). Empty Mass: 322 kg (709 lb). Motor: 1 x X-256. Thrust (vac): 257.500 kN (57,888 lbf). Burn time: 4.40 sec. Length: 3.90 m (12.70 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.
  • Stage2: 1 x Improved Orion-1. Gross Mass: 400 kg (880 lb). Motor: 1 x Orion. Thrust (vac): 13.000 kN (2,922 lbf). Burn time: 32 sec. Length: 1.80 m (5.90 ft). Diameter: 0.35 m (1.14 ft). Propellants: Solid.
Version:

Terrier Orion.
Terrier Orion
Sounding rocket. Status: Active.

The Terrier-Orion was a two-stage, spin-stabilized sounding rocket. It used a Terrier Mk 12 Mod 1 engine for its first stage and an improved Orion motor for its second stage. The Terrier-Orion could loft payloads weighing up to 290 kilograms to altitudes up to 190 kilometers.

The Terrier Mk Mod 1 was a surplus U.S. Navy missile motor; Orion was a surplus U.S. Army missile motor. The Terrier-Orion was 10.7 meters long. The Terrier stage was 46 centimeters in diameter, and the Orion was 36 centimeters in diameter. Payload 159 kg to 190 km or 290 kg to 115 km.

A more powerful version of the Terrier-Orion rocket used the Terrier Mk 70 motor as its first stage. This version was used for two FAA/AST-licensed suborbital launches performed by Astrotech Space Operations/DTI at the Woomera Instrumented Range in Australia in 2001 and 2002. The second flight, in July 2002, successfully flew the HyShot scramjet engine experiment. DTI Associates of Arlington, Virginia, now markets and offers integration services for the Terrier-Orion after purchasing all intellectual property rights to the rocket from SPACEHAB in July 2001.

Launches: 27. Failures: 1. First Launch Date: 1997-05-23. Last Launch Date: 2007-12-17. Apogee: 300 km (180 mi). Liftoff Thrust: 258.000 kN (58,000 lbf). Total Mass: 1,300 kg (2,800 lb). Core Diameter: 0.46 m (1.50 ft). Total Length: 12.80 m (41.90 ft).

  • Stage1: 1 x Black Brant X-1. Gross Mass: 900 kg (1,980 lb). Empty Mass: 322 kg (709 lb). Motor: 1 x X-256. Thrust (vac): 257.500 kN (57,888 lbf). Burn time: 4.40 sec. Length: 3.90 m (12.70 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.
  • Stage2: 1 x Taurus Orion-2. Gross Mass: 400 kg (880 lb). Empty Mass: 111 kg (244 lb). Motor: 1 x Orion. Thrust (vac): 13.000 kN (2,922 lbf). Burn time: 32 sec. Length: 2.70 m (8.80 ft). Diameter: 0.35 m (1.14 ft). Propellants: Solid.
Version:

Terrier Sounding Rocket. Status: Out of production.

Modified single stage Navy Terrier missiles with cameras were used as sounding rockets. They were launched to an altitude of 140 km from Wallops Island, providing a 1,600 km composite photograph of a frontal cloud formation.

Manufacturer: NSPO. Apogee: 30 km (18 mi). Liftoff Thrust: 258.000 kN (58,000 lbf). Total Mass: 1,300 kg (2,800 lb). Core Diameter: 0.55 m (1.80 ft). Total Length: 6.00 m (19.60 ft). Total Production Built: 3000. Flyaway Unit Cost $: 0.062 million. in: 1959 unit dollars.

  • Stage2: 1 x Sounding Rocket-2. Gross Mass: 1,000 kg (2,200 lb). Motor: 1 x NSPO Sustainer. Length: 3.90 m (12.70 ft). Diameter: 0.42 m (1.37 ft). Propellants: Solid.
Version:

Terrier Lynx. Sounding rocket. Status: Active.

Two stage vehicle consisting of 1 x Terrier + 1 x Lynx

The Terrier Lynx was a two-stage, unguided, fin stabilized rocket system which utilized a Terrier mk70 first stage booster and a Lynx rocket motor for the second stage propulsion. The Terrier mk70 motor had four equally spaced modified Ajax fins, and the Lynx motor had four modified Orion fins on the aft end arranged in a cruciform configuration to provide stability.

The basic Terrier mk70 motor was 3.94 m long with a principal diameter of 46 cm. There was a 7.6-cm interstage adapter which allowed for drag separation at Terrier burnout. Typically, the Terrier booster would utilize two spin motors to reduce dispersion and also serve as drag plates. Each Terrier fin was 0.43 square meters in area. Normally, the fins were canted to provide two revolutions per second spin rate at Terrier burnout. The weight of the

The Lynx was 36 cm in diameter and 2.8 m long. The Lynx fins were normally canted to provide for four revolutions per second spin rate at burnout.

The standard payload for the Terrier mk70-Lynx had a principal diameter of 36 cm and utilized a 3:1 ogive nose cone, although an 11 deg total angle cone could also be flown. The envelope of payload lengths that could be flown was similar to the boosted Orion family. The rocket system could carry a 115-kg payload to 378 kilometers and a 230-kg pound payload to 254 kilometers when launched from sea level at an 85 degree launch angle. Standard hardware included a 3:1 ogive nose cone and a capacitive discharge ignition system. Separation systems could be provided to separate the payload from the motor during ascent.

Manufacturer: NAWC. Launches: 4. First Launch Date: 2000-12-19. Last Launch Date: 2002-07-03. Apogee: 200 km (120 mi). Liftoff Thrust: 258.000 kN (58,000 lbf). Total Mass: 1,300 kg (2,800 lb). Core Diameter: 0.46 m (1.50 ft). Total Length: 9.00 m (29.50 ft).

  • Stage1: 1 x Black Brant X-1. Gross Mass: 900 kg (1,980 lb). Empty Mass: 322 kg (709 lb). Motor: 1 x X-256. Thrust (vac): 257.500 kN (57,888 lbf). Burn time: 4.40 sec. Length: 3.90 m (12.70 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.
  • Stage2: 1 x Terrier Lynx-2. Gross Mass: 300 kg (660 lb). Motor: 1 x Lynx. Length: 3.50 m (11.40 ft). Diameter: 0.25 m (0.82 ft). Propellants: Solid.
Version:

Terrier Oriole. Sounding rocket. Status: Active.

SPACEHAB's Astrotech Space Operations developed the Oriole sounding rocket in the late 1990s to provide launch services for commercial and scientific payloads. Oriole was both the first privately developed sounding rocket in the United States and the first new U.S. sounding rocket in 25 years.

The Oriole was a single-stage vehicle with a graphite-epoxy motor manufactured by Alliant Missile Products Company of Rocket Center, West Virginia. It was 396 centimeters long, 56 centimeters in diameter, and generated an average thrust of 92.1 kN. The vehicle provided payloads with 6 to 9 minutes of microgravity during flight. Additionally, it could be combined with other motors to create two-stage sounding rockets (with the Oriole serving as the second stage.

On July 7, 2000, the first Oriole launch took place from NASA WFF. The launch used a two-stage configuration, with the Oriole serving as the second stage and a Terrier Mk 12 motor serving as the first stage. The Oriole sounding rocket reached a peak altitude of 385.6 kilometers 315 seconds after launch during the 10-minute test flight.

In July 2001, SPACEHAB's Astrotech Space Operations sold the Oriole program to DTI Associates of Arlington, Virginia, which integrates the vehicle and offers it commercially.

Manufacturer: DTI Associates. Launches: 2. First Launch Date: 2000-07-07. Last Launch Date: 2005-03-03. Apogee: 370 km (220 mi). Liftoff Thrust: 258.000 kN (58,000 lbf). Total Mass: 1,000 kg (2,200 lb). Core Diameter: 0.56 m (1.83 ft). Total Length: 11.00 m (36.00 ft).

  • Stage1: 1 x Black Brant X-1. Gross Mass: 900 kg (1,980 lb). Empty Mass: 322 kg (709 lb). Motor: 1 x X-256. Thrust (vac): 257.500 kN (57,888 lbf). Burn time: 4.40 sec. Length: 3.90 m (12.70 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.
  • Stage2: 1 x Terrier Oriole-2. Motor: 1 x Oriole. Length: 3.90 m (12.70 ft). Diameter: 0.56 m (1.83 ft). Propellants: Solid.
Version:

Terrier Mk 70 Orion. Sounding rocket. Status: Active.

Launches: 9. Failures: 2. First Launch Date: 2001-10-30. Last Launch Date: 2006-03-30. Apogee: 300 km (180 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 1,300 kg (2,800 lb). Core Diameter: 0.46 m (1.50 ft). Total Length: 12.80 m (41.90 ft).

  • Stage1: 1 x Terrier Mk 70 Oriole-1. Gross Mass: 1,038 kg (2,288 lb). Empty Mass: 290 kg (630 lb). Motor: 1 x TX-664-4. Burn time: 6.20 sec. Length: 3.94 m (12.92 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.
  • Stage2: 1 x Improved Orion-1. Gross Mass: 400 kg (880 lb). Motor: 1 x Orion. Thrust (vac): 13.000 kN (2,922 lbf). Burn time: 32 sec. Length: 1.80 m (5.90 ft). Diameter: 0.35 m (1.14 ft). Propellants: Solid.
Version:

Terrier ASAS. Sounding rocket. Status: Active.

Launches: 1. First Launch Date: 2005-06-28. Last Launch Date: 2005-06-28. Apogee: 275 km (170 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 1,300 kg (2,800 lb). Core Diameter: 0.46 m (1.50 ft). Total Length: 12.00 m (39.00 ft).

  • Stage1: 1 x Terrier Mk 70 Oriole-1. Gross Mass: 1,038 kg (2,288 lb). Empty Mass: 290 kg (630 lb). Motor: 1 x TX-664-4. Burn time: 6.20 sec. Length: 3.94 m (12.92 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.
  • Stage2: 1 x Terrier ASAS-2. Gross Mass: 100 kg (220 lb). Thrust (vac): 7.000 kN (1,574 lbf). Burn time: 15 sec. Length: 0.90 m (2.95 ft). Diameter: 0.53 m (1.73 ft). Propellants: Solid.
Version:

Terrier Mk 70 Oriole. Sounding rocket. Status: Active.

Manufacturer: Astrotech. Launches: 1. First Launch Date: 2005-11-02. Last Launch Date: 2005-11-02. Apogee: 370 km (220 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 1,000 kg (2,200 lb). Core Diameter: 0.46 m (1.50 ft). Total Length: 11.00 m (36.00 ft).

  • Stage1: 1 x Terrier Mk 70 Oriole-1. Gross Mass: 1,038 kg (2,288 lb). Empty Mass: 290 kg (630 lb). Motor: 1 x TX-664-4. Burn time: 6.20 sec. Length: 3.94 m (12.92 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.
  • Stage2: 1 x Terrier Oriole-2. Motor: 1 x Oriole. Length: 3.90 m (12.70 ft). Diameter: 0.56 m (1.83 ft). Propellants: Solid.
Terrier Chronology

1958 December 5 - Wallops Island -. First Terrier sounding flight. Modified Navy Terrier rocket with camera launched to an altitude of 86 miles from Wallops Island, providing a 1,000-mile composite photograph of a frontal cloud formation.

1959 May 1 - Vandenberg -. Terrier ASROC Cajun Terasca FAILURE: Failure. Test mission Agency: USN. Apogee: 0 km ( mi).

1959 June 26 - Vandenberg -. Terrier ASROC Cajun Terasca Radar beacon test Agency: USN. Apogee: 100 km (60 mi).

1959 August 12 - Vandenberg -. Terrier ASROC Cajun Terasca FAILURE: Failure. Ultraviolet Scanner test Agency: USN. Apogee: 0 km ( mi).

1959 September 30 - Vandenberg -. Terrier Asp Tarp Ultraviolet Scanner test Agency: USN. Apogee: 100 km (60 mi).

1962 March 14 - Vandenberg LC-B. Vista-300 test Agency: USN. Apogee: 150 km (90 mi).

1962 December 13 - Vandenberg LC-B. Vista-300 test Agency: USN. Apogee: 150 km (90 mi).

1965 October 20 - San Nicolas -. FAILURE: Failure. Flight test 1 test Agency: NMC. Apogee: 5.00 km (3.10 mi).

1966 March 1 - White Sands -. DAR-3 test Agency: USN. Apogee: 500 km (310 mi).

1966 August 2 - San Nicolas -. Flight test 2 test Agency: NMC. Apogee: 443 km (275 mi).

1974 - Tonopah -. Terrier Nike Sandia NRV Parachute test Agency: Sandia. Apogee: 2.00 km (1.20 mi).

1974 November 11 - Barking Sands -. Terrier Malemute Sandia 497-002 FAILURE: Failure. Test mission Agency: Sandia. Apogee: 10 km (6 mi).

1975 May 12 - Barking Sands -. Terrier Malemute Sandia 497-004 Test mission Agency: Sandia. Apogee: 485 km (301 mi).

1975 June 27 - 20:10 GMT - Wallops Island -. Terrier Malemute NASA 29.02GT FAILURE: Failure. Test mission Agency: NASA. Apogee: 283 km (175 mi).

1976 January 15 - 18:30 GMT - Wallops Island -. Terrier Malemute NASA 12.34CT-GT FAILURE: Failure. Test mission Agency: NASA. Apogee: 81 km (50 mi).

1976 August 11 - 19:12 GMT - Wallops Island -. Terrier Malemute NASA 12.36GT Test mission Agency: NASA. Apogee: 612 km (380 mi).

1976 November 27 - 20:51 GMT - Andoya -. Terrier Malemute NASA 29.05IE Ferdinand 38 (Harang) Aurora mission Agency: NASA. Apogee: 538 km (334 mi).

1977 January 14 - 10:18 GMT - Poker Flat -. Terrier Malemute NASA 29.03AE Aurora / aeronomy / ionosphere mission Agency: NASA. Apogee: 500 km (310 mi).

1977 January 18 - 05:43 GMT - Poker Flat -. Terrier Malemute NASA 29.04UE FAILURE: Failure. Aurora / plasma mission Agency: NASA. Apogee: 11 km (6 mi).

1977 September 10 - Wallops Island -. Terrier Malemute Sandia 497-008 Test mission Agency: Sandia. Apogee: 500 km (310 mi).

1978 February 2 - 08:54 GMT - Poker Flat -. Terrier Malemute NASA 29.08UE Plasma mission Agency: NASA. Apogee: 616 km (382 mi).

1978 March 9 - 08:13 GMT - Poker Flat -. Terrier Malemute NASA 29.07UE Plasma mission Agency: NASA. Apogee: 336 km (208 mi).

1979 January 26 - 11:01 GMT - Poker Flat -. Terrier Malemute NASA 29.13UE FAILURE: Failure. Plasma mission Agency: NASA. Apogee: 186 km (115 mi).

1979 April 15 - 09:31 GMT - Poker Flat -. Terrier Malemute NASA 29.11GE Plasma mission Agency: NASA. Apogee: 671 km (416 mi).

1979 April 18 - 09:09 GMT - Poker Flat -. Terrier Malemute NASA 29.12GE Plasma mission Agency: NASA. Apogee: 500 km (310 mi).

1979 July 16 - 12:31 GMT - Kwajalein -. Terrier Malemute Sandia 497-011 PLUMEX I Aeronomy / Chemical release mission Agency: Sandia. Apogee: 590 km (360 mi).

1979 July 23 - 09:57 GMT - Kwajalein -. Terrier Malemute Sandia 497-012 PLUMEX II Aeronomy / Chemical release mission Agency: Sandia. Apogee: 580 km (360 mi).

1979 October 13 - Barking Sands -. Terrier Malemute Sandia 497-010 Malemute II Test / plasma mission Agency: Sandia. Apogee: 533 km (331 mi).

1980 January 27 - 09:17 GMT - Poker Flat -. Terrier Malemute NASA 29.14UE ARCS 1 Plasma mission Agency: NASA. Apogee: 433 km (269 mi).

1981 December 7 - 00:00 GMT - Cape Parry -. Terrier Malemute NASA 29.17CE CENTAUR Plasma mission Agency: NASA. Apogee: 451 km (280 mi).

1982 January 21 - 01:31 GMT - Cape Parry -. Terrier Malemute NASA 29.18UE Plasma mission Agency: NASA. Apogee: 633 km (393 mi).

1982 March 6 - 08:47 GMT - Poker Flat -. Terrier Malemute NASA 29.16CE Plasma mission Agency: NASA. Apogee: 434 km (269 mi).

1983 March 2 - 02:51 GMT - Punta Lobos -. Terrier Malemute NASA 29.20UE CONDOR Plasma mission Agency: NASA. Apogee: 590 km (360 mi).

1983 March 15 - 02:33 GMT - Punta Lobos -. Terrier Malemute NASA 29.19UE CONDOR Plasma mission Agency: NASA. Apogee: 520 km (320 mi).

1983 November 11 - 21:08 GMT - Andoya -. Terrier Malemute NASA 29.22GE/IE Ferdinand 63 / Polar Leap Aurora mission Agency: NASA. Apogee: 454 km (282 mi).

1984 February 7 - 09:10 GMT - Fort Yukon -. Terrier Malemute NASA 29.21UE Plasma mission Agency: NASA. Apogee: 500 km (310 mi).

1985 January 23 - 09:23 GMT - Sonde Stromfjord -. Terrier Malemute NASA 29.23UE COPE Plasma mission Agency: NASA. Apogee: 500 km (310 mi).

1985 February 10 - 02:11 GMT - Sonde Stromfjord -. Terrier Malemute NASA 29.15UE ARCS 3 Plasma / active mission Agency: NASA. Apogee: 406 km (252 mi).

1985 July 14 - 15:05 GMT - Barking Sands KP. Terrier Malemute Sandia 497-013 ACE I Target Agency: SDIO/MIT-LL. Apogee: 497 km (308 mi).

1985 September 27 - 15:20 GMT - Barking Sands KP. Terrier Malemute Sandia 497-014 ACE II Target Agency: SDIO/MIT-LL. Apogee: 497 km (308 mi).

1985 October 10 - 15:25 GMT - Barking Sands KP. Terrier Malemute Sandia 497-015 ACE III Target Agency: SDIO/MIT-LL. Apogee: 479 km (297 mi).

1985 December 10 - 15:50 GMT - Barking Sands KP. Terrier Malemute Sandia 497-016 ACE IV Target Agency: SDIO/MIT-LL. Apogee: 486 km (301 mi).

1986 April 3 - 10:36 GMT - Poker Flat -. Terrier Malemute NASA 29.24UE Plasma mission Agency: NASA. Apogee: 500 km (310 mi).

1987 February 26 - 23:43 GMT - Sonde Stromfjord -. Terrier Malemute NASA 29.25UE Plasma mission Agency: NASA. Apogee: 500 km (310 mi).

1987 March 5 - 06:32 GMT - Sonde Stromfjord -. Terrier Malemute NASA 29.26UE Plasma mission Agency: NASA. Apogee: 500 km (310 mi).

1989 April 3 - 02:27 GMT - Wallops Island -. Terrier Malemute NASA 29.27UE RED AIR 1 Plasma mission Agency: NASA. Apogee: 379 km (235 mi).

1989 September 4 - Barking Sands -. Terrier Malemute SDIO Starmate Target mission Agency: SDIO. Apogee: 724 km (449 mi).

1989 September 11 - Barking Sands -. Terrier Malemute SDIO Starmate Target mission Agency: SDIO. Apogee: 724 km (449 mi).

1990 March 29 - Wallops Island -. Terrier Malemute SDIO Laser Radar Firefly 1 Target Agency: SDIO. Apogee: 462 km (287 mi).

1990 April 25 - 05:32 GMT - Wallops Island -. Terrier Malemute SDIO BSUV Bow Shock 1 re-entry vehicle test flight Agency: SDIO. Apogee: 721 km (448 mi).

1990 July 30 - 09:48 GMT - Kwajalein RN. Terrier Malemute NASA 29.28UE EQUIS Spread F Plasma mission Agency: NASA. Apogee: 480 km (290 mi).

1990 August 2 - 10:07 GMT - Kwajalein RN. Terrier Malemute NASA 29.29UE EQUIS Spread F Plasma mission Agency: NASA. Apogee: 480 km (290 mi).

1990 October 20 - Wallops Island -. Terrier Malemute SDIO Firefly 2 Target Agency: SDIO. Apogee: 456 km (283 mi).

1991 March 5 - 19:19 GMT - Wallops Island -. Terrier NASA 12.44WT Test mission Agency: NASA. Apogee: 20 km (12 mi).

1992 May 24 - Barking Sands -. CDX (LWIS) Target Agency: SDIO. Apogee: 290 km (180 mi).

1992 September 24 - Point Mugu -. Terrier LEAP Rockwell LEAP FTV-1 (Dummy LEAP) Interceptor mission Agency: USN. Apogee: 30 km (18 mi).

1993 September 27 - Point Mugu -. Terrier LEAP Rockwell LEAP FTV-2 LEAP Mockup Interceptor mission Agency: USN. Apogee: 30 km (18 mi).

1994 April 5 - 18:22 GMT - Wallops Island -. Terrier Improved Orion NASA 12.046WT Test mission Agency: NASA. Apogee: 127 km (78 mi).

1995 March 4 - Atlantic Ocean -. Terrier LEAP Hughes LEAP FTV-3 Interceptor mission Agency: USN. Apogee: 30 km (18 mi). Launched by vessel CG-20 from Aegis NTW test launch area, Atlantic Ocean off S Carolina - Latitude: 33.00 N, Longitude:77.00 W.

1995 March 28 - Atlantic Ocean -. Terrier LEAP Hughes LEAP FTV-4 Interceptor mission Agency: USN. Apogee: 30 km (18 mi). Launched by vessel CG-20 from Aegis NTW test launch area, Atlantic Ocean off S Carolina - Latitude: 33.00 N, Longitude:77.00 W.

1995 June 30 - 18:00 GMT - Wallops Island -. Terrier Improved Orion NASA 12.47WT Test mission Agency: NASA. Apogee: 300 km (180 mi).

1996 November 17 - 13:30 GMT - White Sands LC36. Terrier Improved Orion NASA 41.005GP Test mission Agency: NASA GSFC. Apogee: 150 km (90 mi).

1997 May 23 - 21:44 GMT - Wallops Island -. Terrier Orion NASA 41.13DT MSX? Target Agency: NASA/SMDC. Apogee: 150 km (90 mi).

1997 August 8 - 13:24 GMT - Wallops Island -. Terrier Improved Orion NASA 41.11UE FAILURE: Failure. COORS / ROCKI (CRISTA) Ionosphere / aeronomy mission Agency: NASA GSFC. Apogee: 20 km (12 mi).

1997 September 2 - 07:00 GMT - Anna Plains -. Terrier Improved Orion NASA 41.14DT DUNDEE 1 Target mission Agency: NASA GSFC. Apogee: 300 km (180 mi).

1997 September 5 - 04:00 GMT - Anna Plains -. Terrier Improved Orion NASA 41.15DT DUNDEE 2 Target mission Agency: NASA GSFC. Apogee: 300 km (180 mi).

1997 September 10 - 02:00 GMT - Anna Plains -. Terrier Improved Orion NASA 41.16DT DUNDEE 3 Target mission Agency: NASA GSFC. Apogee: 300 km (180 mi).

1997 September 11 - 20:15 GMT - Anna Plains -. Terrier Improved Orion NASA 41.17DT DUNDEE 4 (MSX) Target mission Agency: NASA GSFC. Apogee: 300 km (180 mi).

1997 November 5 - 20:02 GMT - Andoya -. Terrier Improved Orion NASA 41.04IE Ionosphere mission Agency: NASA GSFC. Apogee: 120 km (70 mi).

1998 February 25 - 07:50 GMT - Arecibo -. Terrier Improved Orion NASA 41.08UE EDDY Ionosphere mission Agency: NASA GSFC. Apogee: 128 km (79 mi).

1998 December 15 - Jiu Peng AB -. Sounding Rocket 1 Test flight test Agency: NSPO. Apogee: 250 km (150 mi).

1999 December 17 - 17:00 GMT - Wallops Island -. Terrier Improved Orion NASA 41.020NM MG. Pool Boiling Microgravity mission Agency: NASA GSFC. Apogee: 168 km (104 mi).

2000 June 8 - Barking Sands -. PACBLITZ 00 Target mission Agency: USN. Apogee: 10 km (6 mi).

2000 June 8 - Barking Sands -. PACBLITZ 00 Target mission Agency: USN. Apogee: 10 km (6 mi).

2000 July 7 - 10:25 GMT - Wallops Island -. Test mission Agency: NASA GSFC. Apogee: 368 km (228 mi).

2000 October 13 - 14:45 GMT - White Sands -. Terrier Improved Orion NASA 41.021DP Test mission Agency: NASA GSFC. Apogee: 100 km (60 mi).

2000 December 19 - 11:57 GMT - Wallops Island -. Terrier Lynx NASA 12.50DP NAWC test Agency: NASA/SMDC. Apogee: 300 km (180 mi).

2001 September 27 - 16:10 GMT - Barking Sands -. Terrier Lynx NASA 42.01DP Test mission Agency: NASA/SMDC. Apogee: 300 km (180 mi).

2001 October 24 - 16:00 GMT - Jiu Peng AB -. Sounding Rocket 2 FAILURE: Failure. TMA Aeronomy mission Agency: NSPO. Apogee: 2.00 km (1.20 mi).

2001 October 30 - 02:31 GMT - Woomera -. Terrier Mk 70 Orion T-Orion 5A FAILURE: Failure. Hyshot 1 'Hilary' Technology mission Agency: UQU. Apogee: 100 km (60 mi). First launch attempt in the HyShot Flight Program. The scramjet payload was to be used to verify pressure measurements made of supersonic combustion in The University of Queensland's T4 shock tunnel by those made in an actual flight. A failure of stabilising fins meant that the rocket fell far short of the planned 330-km apogee and the scramjet experiment was not conducted.

2002 June 5 - 10:43 GMT - White Sands -. Terrier Orion NASA 41.023UE Plasma mission Agency: NASA GSFC. Apogee: 130 km (80 mi).

2002 June 5 - 11:13 GMT - White Sands -. Terrier Orion NASA 41.022UE Plasma mission Agency: NASA GSFC. Apogee: 130 km (80 mi).

2002 July 1 - 23:56 GMT - Andoya -. Terrier Orion NASA 41.032GE MM-MW-08 MacWAVE Plasma mission Agency: NASA GSFC. Apogee: 130 km (80 mi).

2002 July 2 - 21:45 GMT - Barking Sands -. Terrier Lynx NASA 42.02DP PACBLITZ 02 Target mission Agency: NASA GSFC. Apogee: 300 km (180 mi).

2002 July 3 - 21:05 GMT - Barking Sands -. Terrier Lynx NASA 42.03DP PACBLITZ 02 Target mission Agency: NASA GSFC. Apogee: 300 km (180 mi).

2002 July 5 - 00:47 GMT - Andoya -. Terrier Orion NASA 41.033GE MM-MW-23 MacWAVE Plasma mission Agency: NASA GSFC. Apogee: 132 km (82 mi).

2002 July 30 - 02:05 GMT - Woomera -. Hyshot 2 'Hans' Technology mission Agency: UQU. Apogee: 314 km (195 mi). In the second launch of the HyShot program, the Terrier-Orion Mk70 rocket boosted the payload, which remain attached to the second stage Orion motor, toward a planned apogee of 330 km. After peaking at 314 km, the trajectory was designed so that the payload was moving at Mach 7.6 between 35 km and 23 km on the way down, at which point the measurements of supersonic combustion were made. This was claimed to be the first successful test of a scramjet in flight.

2002 November 20 - 01:33 GMT - Wallops Island -. Terrier Orion NASA 41.039DP VALPE (fairing) test Agency: NASA GSFC. Apogee: 135 km (83 mi).

2003 January 24 - 20:50 GMT - Kiruna -. Terrier Orion NASA 41.030GE MacWAVE Plasma mission Agency: NASA GSFC. Apogee: 131 km (81 mi).

2003 January 28 - 18:32 GMT - Kiruna -. Terrier Orion NASA 41.031GE MacWAVE Plasma / aeronomy mission Agency: NASA GSFC. Apogee: 130 km (80 mi).

2003 March 25 - 10:09 GMT - Poker Flat LC3. Terrier Improved Orion NASA 41.034UE HEX V Aurora / chemical release mission Agency: NASA GSFC. Apogee: 180 km (110 mi).

2003 March 27 - 12:10 GMT - Poker Flat LC5. Terrier Improved Orion NASA 41.028UE FAILURE: Failure. JOULE Aurora / chemical release mission Agency: NASA GSFC. Apogee: 10 km (6 mi).

2003 March 27 - 12:13 GMT - Poker Flat LC2. Terrier Improved Orion NASA 41.029UE JOULE Aurora / chemical release mission Agency: NASA GSFC. Apogee: 180 km (110 mi).

2003 June 10 - 06:31 GMT - Wallops Island -. Terrier Malemute NASA 29.035UP DEBI (Bowshock) Technology mission Agency: NASA GSFC. Apogee: 600 km (370 mi).

2003 June 30 - 03:25 GMT - Wallops Island -. Terrier Improved Orion NASA 41.036UE Release M / Dtr Aeronomy / Chemical release mission Agency: NASA GSFC. Apogee: 202 km (125 mi).

2003 June 30 - 05:41 GMT - Wallops Island -. Terrier Improved Orion NASA 41.037UE Release M / Dtr Aeronomy / Chemical release mission Agency: NASA GSFC. Apogee: 206 km (128 mi).

2003 June 30 - 07:07 GMT - Wallops Island -. Terrier Improved Orion NASA 41.038UE Release M / Dtr Aeronomy / Chemical release mission Agency: NASA GSFC. Apogee: 204 km (126 mi).

2003 July 15 - 07:02 GMT - White Sands -. Terrier Improved Orion NASA 41.025UE CWAS Aeronomy mission Agency: NASA GSFC. Apogee: 130 km (80 mi).

2003 July 15 - 07:32 GMT - White Sands -. Terrier Improved Orion NASA 41.024UE CWAS Aeronomy mission Agency: NASA GSFC. Apogee: 130 km (80 mi).

2003 August 1 - 10:25 GMT - Wallops Island -. Terrier Mk 70 Orion NASA 12.052GT NMACS test Agency: NASA GSFC. Apogee: 204 km (126 mi).

2003 August 20 - 11:05 GMT - Wallops Island -. Terrier Orion NASA 41.040DP VALPE-2 test Agency: NASA GSFC. Apogee: 135 km (83 mi).

2003 October 3 - 14:30 GMT - Wallops Island -. Terrier Improved Orion NASA 41.035UE SPIRIT 2 Aeronomy / Chemical release mission Agency: NASA GSFC. Apogee: 130 km (80 mi).

2003 October 18 - 19:00 GMT - Wallops Island -. Dummy Scramjet test Agency: DARPA. Apogee: 20 km (12 mi).

2003 October 24 - 10:45 GMT - Wallops Island -. Terrier Mk 70 Orion NASA 12.053GT NMACS test Agency: NASA GSFC. Apogee: 156 km (96 mi).

2003 December 24 - 15:25 GMT - Jiu Peng AB -. Sounding Rocket 3 TMA Aeronomy mission Agency: NSPO. Apogee: 265 km (164 mi).

2004 April 13 - 03:30 GMT - White Sands -. Terrier Mk 70 Orion NASA 12.54GT NMACS test Agency: NASA GSFC. Apogee: 122 km (75 mi).

2004 August 7 - 08:52 GMT - Kwajalein -. Terrier Malemute NASA 29.037UE EQUIS II Ionosphere mission Agency: NASA GSFC. Apogee: 450 km (270 mi).

2004 August 7 - 09:07 GMT - Kwajalein -. Terrier Improved Orion NASA 41.043UE EQUIS II Ionosphere mission Agency: NASA GSFC. Apogee: 130 km (80 mi).

2004 August 7 - 09:11 GMT - Kwajalein -. Terrier Improved Orion NASA 41.045UE EQUIS II Ionosphere mission Agency: NASA GSFC. Apogee: 130 km (80 mi).

2004 August 15 - 08:21 GMT - Kwajalein -. Terrier Malemute NASA 29.036UE EQUIS II Ionosphere mission Agency: NASA GSFC. Apogee: 450 km (270 mi).

2004 August 15 - 08:47 GMT - Kwajalein -. Terrier Improved Orion NASA 41.044UE EQUIS II Ionosphere mission Agency: NASA GSFC. Apogee: 130 km (80 mi).

2004 August 15 - 08:51 GMT - Kwajalein -. Terrier Improved Orion NASA 41.046UE FAILURE: Failure. EQUIS II Ionosphere mission Agency: NASA GSFC. Apogee: 100 km (60 mi).

2004 August 27 - 22:42 GMT - Kwajalein -. Terrier Improved Orion NASA 41.041UE EQUIS II Ionosphere mission Agency: NASA GSFC. Apogee: 130 km (80 mi).

2004 September 7 - 23:56 GMT - Kwajalein -. Terrier Improved Orion NASA 41.048UE EQUIS II Ionosphere mission Agency: NASA GSFC. Apogee: 130 km (80 mi).

2004 September 17 - 08:12 GMT - Kwajalein -. Terrier Improved Orion NASA 41.047UE EQUIS II Ionosphere mission Agency: NASA GSFC. Apogee: 130 km (80 mi).

2004 September 20 - 23:30 GMT - Kwajalein -. Terrier Improved Orion NASA 41.042UE EQUIS II Ionosphere mission Agency: NASA GSFC. Apogee: 130 km (80 mi).

2004 September 23 - 03:00 GMT - White Sands -. Terrier Mk 70 Orion NASA 12.56GT FAILURE: Failure. NMACS test Agency: NASA GSFC. Apogee: 120 km (70 mi).

2004 November 24 - 03:00 GMT - White Sands -. Terrier Orion NASA 12.061GT FAILURE: Failure. Test mission Agency: NASA GSFC. Apogee: 20 km (12 mi).

2004 December 14 - 14:30 GMT - Jiu Peng AB -. Sounding Rocket 4 Space science Ionosphere / aeronomy mission Agency: NSPO. Apogee: 265 km (164 mi).

2005 February 2 - 20:57 GMT - Barking Sands -. Terrier Orion NASA 41.58DR Target mission Agency: NASA/NAWC. Apogee: 130 km (80 mi).

2005 March 1 - 23:13 GMT - Barking Sands -. Terrier Orion NASA 41.59DR Target mission Agency: NASA/NAWC. Apogee: 130 km (80 mi).

2005 March 2 - 21:11 GMT - Barking Sands -. Terrier Orion NASA 41.60DR Target mission Agency: NASA/NAWC. Apogee: 130 km (80 mi).

2005 March 3 - 22:05 GMT - Barking Sands -. Terrier Oriole NASA 45.01DR Target mission Agency: NASA/NAWC. Apogee: 300 km (180 mi).

2005 May 5 - 09:35 GMT - Wallops Island -. Terrier Orion NASA 41.57DP MCAFT-1 / IBSi Missile defense / biology mission Agency: NASA GSFC. Apogee: 156 km (96 mi).

2005 June 28 - 22:54 GMT - Wallops Island -. Terrier ASAS NASA 12.060GT Test flight test Agency: NASA GSFC. Apogee: 275 km (170 mi).

2005 November 2 - 22:34 GMT - Barking Sands -. Terrier Mk 70 Oriole NASA 45.02DR Target Agency: NASA/NAWC. Apogee: 300 km (180 mi).

2005 November 14 - 20:30 GMT - White Sands -. Terrier Improved Orion NASA 41.66DR Target Agency: NASA/NAWC. Apogee: 130 km (80 mi).

2005 November 18 - 20:13 GMT - White Sands -. Terrier Improved Orion NASA 41.67DR Target Agency: NASA/NAWC. Apogee: 130 km (80 mi).

2005 December 10 - 11:30 GMT - Wallops Island -. FASTT Scramjet mission Agency: NASA/DARPA. Apogee: 19 km (11 mi).

2005 December 20 - 19:30 GMT - Wallops Island -. Terrier Orion NASA 12.63GT Water recovery test Agency: NASA GSFC. Apogee: 100 km (60 mi).

2006 January 18 - 11:48 GMT - Jiu Peng AB -. Sounding Rocket 5 Space science Ionosphere / aeronomy mission Agency: NSPO. Apogee: 282 km (175 mi).

2006 March 25 - 03:15 GMT - Woomera -. HyShot 3 Agency: UQU. Apogee: 325 km (201 mi). The 100-kg test British-design scramjet engine was boosted to an altitude of 314 km during a 10-minute flight. It and the attached second stage then were re-oriented to point back to the Earth. The scramjet was successfully ignited at a speed of Mach 8 in the tiny six-second window of opportunity shortly before impact.

2006 March 30 - 02:40 GMT - Woomera -. Hyshot 4 (JAXA) Agency: UQU. Apogee: 290 km (180 mi). A repeat of the test four days earlier, this time with a Japanese-designed scramjet. The nosecone of the rocket failed to jettison and therefore scramjet ignition was not achieved. The scramjet and second stage remains were located in the desert and recovered after only 20 minutes of searching.

2006 April 5 - 12:00 GMT - White Sands -. Terrier Improved Orion NASA 41.068NT Descent imagery / RSO Planetary test Agency: NASA GSFC. Apogee: 76 km (47 mi).

2006 May 22 - 09:30 GMT - White Sands -. Terrier Improved Orion NASA 12.58GT ACS test Agency: NASA GSFC. Apogee: 150 km (90 mi).

2006 June 5 - 16:05 GMT - White Sands -. Terrier Improved Orion NASA 41.073DR Target Agency: NASA/NAWC. Apogee: 130 km (80 mi).

2006 June 7 - 22:00 GMT - Barking Sands -. Terrier Improved Orion NASA 41.071DR Target Agency: NASA/NAWC. Apogee: 130 km (80 mi).

2006 June 8 - 16:00 GMT - White Sands -. Terrier Improved Orion NASA 41.074DR DUNDEE target Target Agency: NASA/NAWC. Apogee: 130 km (80 mi).

2006 June 23 - 23:02 GMT - Barking Sands -. Terrier Improved Orion NASA 41.072DR MDA TRACKEX Target Agency: NASA/NAWC. Apogee: 130 km (80 mi).

2006 July 1 - 06:39 GMT - Andoya -. Terrier Improved Orion NASA 41.056UO ESPRIT (SPIRIT 3) Ionosphere / plasma mission Agency: NASA GSFC. Apogee: 200 km (120 mi).

2006 November 16 - Barking Sands -. Terrier Orion ARAV-B Target Agency: USN. Apogee: 150 km (90 mi).

2007 January 19 - 12:30 GMT - Poker Flat -. Terrier Improved Orion NASA 41.064UE JOULE II Aurora mission Agency: NASA GSFC. Apogee: 200 km (120 mi).

2007 January 19 - 12:46 GMT - Poker Flat -. Terrier Improved Orion NASA 41.065UE JOULE II Aurora mission Agency: NASA GSFC. Apogee: 200 km (120 mi).

2007 February 14 - 09:22 GMT - Poker Flat -. Terrier Orion NASA 41.061 HEX-II V-1 Aeronomy mission Agency: NASA GSFC. Apogee: 200 km (120 mi).

2007 February 14 - 09:36 GMT - Poker Flat -. Terrier Orion NASA 41.063 HEX-II V-2 Aeronomy mission Agency: NASA GSFC. Apogee: 200 km (120 mi).

2007 February 14 - 09:38 GMT - Poker Flat -. Terrier Orion NASA 41.062 HEX-II V-3 Aeronomy mission Agency: NASA GSFC. Apogee: 200 km (120 mi).

2007 April 26 - 21:31 GMT - Barking Sands -. Terrier Orion ARAV-A? FTM-11 Target Agency: USN. Apogee: 160 km (90 mi).

2007 June 15 - Barking Sands -. Terrier Orion ARAV Target Agency: USN/Sandia. Apogee: 160 km (90 mi).

2007 June 15 - Barking Sands -. Terrier Orion ARAV Target Agency: USN/Sandia. Apogee: 160 km (90 mi).

2007 June 21 - 05:38 GMT - White Sands -. Terrier Improved Orion NASA 12.059GT Star tracker / ACS test Agency: NASA GSFC. Apogee: 130 km (80 mi).

2007 August 3 - 22:51 GMT - Andoya -. Terrier Improved Orion NASA 41.069 MASS 1 (NLCs) Aeronomy mission Agency: NASA GSFC. Apogee: 130 km (80 mi).

2007 August 6 - 22:56 GMT - Andoya -. Terrier Improved Orion NASA 41.070 MASS 2 (NLCs) Aeronomy mission Agency: NASA GSFC. Apogee: 130 km (80 mi).

2007 September 6 - 21:09 GMT - Wallops Island -. Terrier Improved Orion NASA 41.055NP IVRE test Agency: NASA GSFC. Apogee: 130 km (80 mi).

2007 November 6 - 04:12 GMT - Barking Sands -. Terrier Orion Aegis Target PAC-2 target Agency: USN. Apogee: 150 km (90 mi). A Standard Missile-3 was launched from the Aegis cruiser CG 70 USS Lake Erie in a Missile Defense Agency ballistic missile flight test. This was a successful multiple simultaneous engagement involving two ballistic missile targets.

2007 November 6 - 04:12 GMT - Barking Sands -. Terrier Orion Aegis Target PAC-2 target Agency: USN. Apogee: 150 km (90 mi).

2007 November 15 - Barking Sands -. Terrier Orion ARAV? Target Agency: USN. Apogee: 160 km (90 mi).

2007 December 17 - 22:05 GMT - Barking Sands -. Terrier Orion Aegis Target Agency: USN. Apogee: 150 km (90 mi).

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© Mark Wade, 1997 - 2008 except where otherwise noted.