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Engine Model: Star 63. Designer: Thiokol. Gross Mass: 3,697 kg (8,150 lb). Empty Mass: 431 kg (950 lb). Propellants: Solid. Thrust(vac): 107.200 kN (24,100 lbf). Isp: 282 sec. Burn time: 120 sec. Diameter: 1.60 m (5.20 ft). Length: 1.83 m (6.00 ft). Chambers: 1. Area Ratio: 27.33. Country: USA. First Flight: 1990. Last Flight: 2006. Flown: 104.

Used in Shuttle,Titan 34D.

Engine Model: Star 63D. Manufacturer Name: TU-936. Other Designations: 118-KS-19,050. Designer: Thiokol. Gross Mass: 3,499 kg (7,713 lb). Empty Mass: 248 kg (546 lb). Propellants: Solid. Thrust(vac): 84.739 kN (19,050 lbf). Isp: 283 sec. Burn time: 118 sec. Diameter: 1.60 m (5.25 ft). Chambers: 1. Country: USA. Status: In Production. Flown: 8.00.

Perigee motor has successfully delivered two payloads to elliptical transfer orbit with no failures. Given a range of propellant loads, the STAR 63D payload capability ranges from 3,080 to 4,588 pounds at a constant velocity of 8,012 feet per second. Motor components are of proven design features and material, thus maximizing reliability. Total impulse 921,828 kgf-s. Propellant mass fraction 0.929.

Engine Model: Star 63F. Manufacturer Name: TE-M-963. Other Designations: 120-KS-23,520. Designer: Thiokol. Gross Mass: 4,590 kg (10,110 lb). Empty Mass: 326 kg (718 lb). Propellants: Solid. Thrust(vac): 104.627 kN (23,521 lbf). Isp: 297 sec. Burn time: 120 sec. Diameter: 1.60 m (5.20 ft). Length: 1.78 m (5.84 ft). Chambers: 1. Country: USA. Status: In Production. Flown: 5.00.

Provides perigee kick for the McDonnell PAM-D2 system.. Another version is Star 63D (TU-936). Perigee motor has successfully completed development and qualification and is in production. It can be offloaded to a propellant weight of 1952 kg. Motor components are of proven design features and material, thus maximizing reliability. Total impulse 1,277,319 kgf-s. Propellant mass fraction 0.929.

Star 63 used on Rocket Stages
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