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Model: Burner 2. Gross Mass: 774 kg (1,706 lb). Empty Mass: 116 kg (255 lb). Thrust (vac): 43.551 kN (9,791 lbf). Isp: 285 sec. Burn time: 42 sec. Propellants: Solid. Isp(sl): 220 sec. Diameter: 0.66 m (2.16 ft). Span: 0.66 m (2.16 ft). Length: 0.84 m (2.75 ft). Country: USA. No Engines: 1. Motor: Star 37. Status: Study 1965. Cost $ : 3.480 million. First Flight: 1960. Last Flight: 1987. No Launched: 108.

Burner II was a launch vehicle upper stage developed by Boeing for the Air Force Space Systems Division. It was the first solid-fuel upper stage with full control and guidance capability developed for general space applications. Burner II was designed for use with the Thor booster, but was readily adapted for use on the complete range of standard launch vehicles. Its general assignment was to place small- and medium size payloads into orbit. The Burner II motor, guidance system and reaction control system were integrated to provide attitude stability and precise control of flight rate and burnout velocity for orbital injection and earth-escape missions. Boeing had delivered 8 flight vehicles under its original contract. Under terms of a follow-on contract, it built 6 additional flight models. Four Thor-Burner II combinations were launched successfully from Vandenberg Air Force Base, California. The third launch placed 2 unclassified satellites in Earth orbit. A SECOR satellite, built for the U.S. Army Corps of Engineers by the Cubic Corporation, and an Aurora satellite, developed by Rice University for the Office of Naval Research, were placed in circular orbits 3,300 km above the Earth. As integration contractor for the Air Force Space Experiment Support Program (SESP) Office, Boeing designed, built and tested the injection stage, or "payload dispenser," which carried the 2 satellites on top of a standard Burner II stage and placed them in precise orbits. The satellites were mounted on opposite sides of the injection stage, which housed a640 kgf thrust, solid-propellant rocket motor. The Burner II was used as an upper stage by NASA for deep space probes. Prime Contractor: The Boeing Company. Major Subcontractors Thiokol Chemical Corporation (solid rocket motor); Honeywell Inc. (pre-programmed inertial guidance system); Walter Kidde Co. (reaction control system).

Model: Star 37B. Gross Mass: 718 kg (1,582 lb). Empty Mass: 64 kg (141 lb). Thrust (vac): 45.000 kN (10,116 lbf). Propellants: Solid. Diameter: 0.94 m (3.08 ft). Length: 1.50 m (4.90 ft). Country: USA. No Engines: 1. Motor: Star 37B. Status: Retired 1976. First Flight: 1968. Last Flight: 1976. No Launched: 23. Used as: Star 37. Other designations: Star 37. Release conditions: Thiokol.

Model: Star 37C. Gross Mass: 1,048 kg (2,310 lb). Empty Mass: 83 kg (182 lb). Thrust (vac): 45.000 kN (10,116 lbf). Propellants: Solid. Diameter: 0.94 m (3.08 ft). Length: 1.50 m (4.90 ft). Country: USA. No Engines: 1. Motor: Star 37C. Status: Retired 1973. First Flight: 1972. Last Flight: 1973. No Launched: 2. Used as: Star 37. Release conditions: Thiokol.

Model: Star 37D. Gross Mass: 718 kg (1,582 lb). Empty Mass: 64 kg (141 lb). Thrust (vac): 45.000 kN (10,116 lbf). Propellants: Solid. Diameter: 0.94 m (3.08 ft). Length: 1.50 m (4.90 ft). Country: USA. No Engines: 1. Motor: Star 37D. Status: Retired 1977. First Flight: 1973. Last Flight: 1977. No Launched: 6. Used as: Star 37. Release conditions: Thiokol.

Model: Star 37E. Gross Mass: 1,123 kg (2,475 lb). Empty Mass: 83 kg (182 lb). Thrust (vac): 68.000 kN (15,287 lbf). Burn time: 42 sec. Propellants: Solid. Diameter: 0.94 m (3.08 ft). Length: 1.70 m (5.50 ft). Country: USA. No Engines: 1. Motor: Star 37E. Status: Retired 1987. First Flight: 1974. Last Flight: 1987. No Launched: 30. Used as: Star 37. Release conditions: Thiokol.

Model: Burner 3. Gross Mass: 1,243 kg (2,740 lb). Empty Mass: 168 kg (370 lb). Thrust (vac): 51.151 kN (11,499 lbf). Isp: 297 sec. Burn time: 60 sec. Propellants: Solid. Isp(sl): 230 sec. Diameter: 0.94 m (3.08 ft). Span: 0.94 m (3.08 ft). Length: 1.86 m (6.10 ft). Country: USA. No Engines: 1. Motor: Star 37X. Status: Out of Production. Cost $ : 4.350 million.

Model: Star 37XE. Gross Mass: 900 kg (1,980 lb). Empty Mass: 67 kg (147 lb). Thrust (vac): 45.000 kN (10,116 lbf). Burn time: 66 sec. Propellants: Solid. Diameter: 0.94 m (3.08 ft). Length: 1.70 m (5.50 ft). Country: USA. No Engines: 1. Motor: Star 37XE. Status: Retired 1980. First Flight: 1976. Last Flight: 1980. No Launched: 5. No Failed: 1. Used as: Star 37. Release conditions: Thiokol.

Model: Star 37N. Gross Mass: 623 kg (1,373 lb). Empty Mass: 64 kg (141 lb). Thrust (vac): 45.000 kN (10,116 lbf). Propellants: Solid. Diameter: 0.94 m (3.08 ft). Length: 1.70 m (5.50 ft). Country: USA. No Engines: 1. Motor: Star 37N. Status: Retired 1981. First Flight: 1981. Last Flight: 1981. No Launched: 2. Used as: Star 37. Other designations: Star 37E. Release conditions: Thiokol.

Model: Star 37S. Gross Mass: 711 kg (1,567 lb). Empty Mass: 53 kg (116 lb). Thrust (vac): 45.000 kN (10,116 lbf). Propellants: Solid. Diameter: 0.94 m (3.08 ft). Length: 1.70 m (5.50 ft). Country: USA. No Engines: 1. Motor: Star 37S. Status: U. Used as: Star 37. Release conditions: Thiokol.

Model: Star 37F. Gross Mass: 934 kg (2,059 lb). Empty Mass: 67 kg (147 lb). Thrust (vac): 55.500 kN (12,477 lbf). Burn time: 42 sec. Propellants: Solid. Diameter: 0.94 m (3.08 ft). Length: 1.70 m (5.50 ft). Country: USA. No Engines: 1. Motor: Star 37F. Status: U. Used as: Star 37. Release conditions: Thiokol.

Model: Star 37XF. Gross Mass: 953 kg (2,101 lb). Empty Mass: 68 kg (149 lb). Thrust (vac): 45.000 kN (10,116 lbf). Propellants: Solid. Diameter: 0.94 m (3.08 ft). Length: 1.70 m (5.50 ft). Country: USA. No Engines: 1. Motor: Star 37XF. Status: U. Used as: Star 37. Release conditions: Thiokol.

Model: Star 37XFP. Gross Mass: 955 kg (2,105 lb). Empty Mass: 71 kg (156 lb). Thrust (vac): 31.500 kN (7,081 lbf). Burn time: 66 sec. Propellants: Solid. Diameter: 0.94 m (3.08 ft). Length: 1.70 m (5.50 ft). Country: USA. No Engines: 1. Motor: Star 37XFP. Status: U. Used as: Star 37. Release conditions: Thiokol.

Model: Star 37FM. Gross Mass: 1,147 kg (2,528 lb). Empty Mass: 81 kg (178 lb). Thrust (vac): 47.900 kN (10,768 lbf). Burn time: 63 sec. Propellants: Solid. Diameter: 0.94 m (3.08 ft). Length: 1.70 m (5.50 ft). Country: USA. No Engines: 1. Motor: Star 37FM. Status: Active. First Flight: 1998. Last Flight: 2001. No Launched: 5. Used as: Star 37. Release conditions: Thiokol.

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