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Star 37
Thiokol solid rocket engine. Total impulse 161,512 kgf-sec. Motor propellant mass fraction 0.899. First flight 1963. Solid propellant rocket stage. 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.
AKA: Burner 2;TE-M-364-1. Status: First flight 1963. Number: 180 . Thrust: 43.50 kN (9,779 lbf). Gross mass: 621 kg (1,369 lb). Unfuelled mass: 63 kg (138 lb). Specific impulse: 260 s. Specific impulse sea level: 220 s. Burn time: 42 s. Height: 0.84 m (2.75 ft). Diameter: 0.66 m (2.16 ft).
Thrust (sl): 33.600 kN (7,554 lbf). Thrust (sl): 3,428 kgf.
Subtopics
| Star 37XF 8 Thiokol solid rocket engine. Out of Production. Total impulse 238,809 kgf-sec. Motor propellant mass fraction 0.924. |
| Star 37B Thiokol solid rocket engine. Out of Production. Total impulse 189,489 kgf-sec. Motor propellant mass fraction 0.91. |
| Star 37C Thiokol solid rocket engine. Out of Production. Total impulse 275,959 kgf-sec. Motor propellant mass fraction 0.921. |
| Star 37D Thiokol solid rocket engine. Out of Production. Total impulse 189,489 kgf-sec. Motor propellant mass fraction 0.91. |
| Star 37E Thiokol solid rocket engine. Out of Production. Total impulse 296,635 kgf-sec. Motor propellant mass fraction 0.926. |
| Star 37F Thiokol solid rocket engine. Out of Production. Total impulse 249,177 kgf-sec. Motor propellant mass fraction 0.928. |
 | Star 37XF Thiokol solid rocket engine. Out of Production. Total flown included in total for Star-37XF-8. Total impulse 259,123 kgf-sec. Motor propellant mass fraction 0.929. |
| Star 37G Thiokol solid rocket engine. Out of Production. Total impulse 304,620 kgf-sec. Motor propellant mass fraction 0.925. |
 | Star 37FM Thiokol solid rocket engine. In Production. Apogee kick motor for the FLTSTACOM satellite. The motor case contained the same volume as the discontinued STAR 37E. |
| Star 37N Thiokol solid rocket engine. Out of Production. Total impulse 162,102 kgf-sec. Motor propellant mass fraction 0.898. |
| Star 37XFP Thiokol solid rocket engine. In Production. Orbit insertion motor qualified for Global Positioning Satellite. Used as a replacement for the discontinued STAR 37F. Propellant: 884 kg of AP/HTPB/Al in 6Al-4V titanium case. |
| Star 37S Thiokol solid rocket engine. Out of Production. Total impulse 190,590 kgf-sec. Motor propellant mass fraction 0.925. |
| Star 37X Thiokol solid rocket engine. Out of Production. Total impulse 310,668 kgf-sec. Motor propellant mass fraction 0.928. |
| Star 37Y Thiokol solid rocket engine. Out of Production. Total impulse 317,856 kgf-sec. Motor propellant mass fraction 0.93. |
Country:
USA.
Spacecraft:
GPS Block 2R.
Launch Vehicles:
Titan 3BAS2,
Atlas Agena D,
Thor Burner 2,
Thor Delta J,
Thor Delta M,
Thor Delta M6,
Delta 0900,
Delta 1914,
Delta 2914,
Delta 3914,
N-2,
N-2 (2),
Delta 0100,
Delta 1000,
Thor Burner,
Delta 2000,
Delta 3000.
Propellants:
Solid.
Stages:
Star 37.
Agency:
Thiokol.
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