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Engine Model: Star 48. Manufacturer Name: TE-M-711-3. Designer: Thiokol. Gross Mass: 2,114 kg (4,660 lb). Empty Mass: 114 kg (251 lb). Propellants: Solid. Thrust(vac): 67.200 kN (15,107 lbf). Isp: 287 sec. Burn time: 88 sec. Diameter: 1.24 m (4.06 ft). Length: 2.04 m (6.69 ft). Chambers: 1. Chamber Pressure: 40.00 bar. Area Ratio: 49.00. Country: USA. First Flight: 1982. Last Flight: 2006. Flown: 125.

Used in Delta 3900; Conesotga; PAM-S; PAM-D. Total flown included in total for Star-48-8. Total impulse 575,682 kgf-sec. Motor propellant mass fraction 0.946.

Engine Model: Star 48 8. Manufacturer Name: TE-M-711-8. Designer: Thiokol. Gross Mass: 2,116 kg (4,664 lb). Empty Mass: 116 kg (255 lb). Propellants: Solid. Isp: 293 sec. Diameter: 1.24 m (4.08 ft). Chambers: 1. Country: USA. Status: Out of Production. Flown: 49.

Total impulse 587,784 kgf-sec. Motor propellant mass fraction 0.945.

Engine Model: Star 48A l. Manufacturer Name: TE-M-799. Designer: Thiokol. Gross Mass: 2,582 kg (5,692 lb). Empty Mass: 152 kg (335 lb). Propellants: Solid. Isp: 290 sec. Diameter: 1.24 m (4.08 ft). Chambers: 1. Country: USA. Status: In Production. Flown: 1.00.

Total impulse 709,062 kgf-sec. Motor propellant mass fraction 0.941.

Engine Model: Star 48A s. Manufacturer Name: TE-M-799-1. Other Designations: 87.2-KS-17,335. Designer: Thiokol. Gross Mass: 2,574 kg (5,674 lb). Empty Mass: 144 kg (317 lb). Propellants: Solid. Thrust(vac): 77.109 kN (17,335 lbf). Isp: 283 sec. Burn time: 87 sec. Diameter: 1.24 m (4.08 ft). Chambers: 1. Country: USA. Status: In Production.

Short nozzle upper-stage motor is designed to fit within the dimensional envelope of the long nozzle Total flown included in total for Star-48A-l. Total impulse 693,030 kgf-sec. Motor propellant mass fraction 0.944.

Engine Model: Star 48B. Manufacturer Name: TE-M-799. Other Designations: 87.2-KS-17,735. Designer: Thiokol. Gross Mass: 2,137 kg (4,711 lb). Empty Mass: 126 kg (277 lb). Propellants: Solid. Thrust(vac): 66.000 kN (14,837 lbf). Isp: 286 sec. Burn time: 87 sec. Diameter: 1.25 m (4.08 ft). Length: 2.03 m (6.67 ft). Chambers: 1. Country: USA. Status: In Production.

Long nozzle upper-stage motor is qualified for the McDonnell Payload Assist Module (PAM) Delta. The basic version for Delta-launched missions contains 2011 kg of propellant (an increase of 11 kg over STAR 48) and has the same 80-inch length as the Delta version of the STAR 48. The design incorporates the same high-energy propellant and high-strength case as the STAR 48. The semi-submerged nozzle uses a carbon-phenolic exit cone. Propellant: 2011 kg charge of AP/HTPB/Al in 6Al-4V titanium case. Total impulse 591,142 kgf-s. Propellant mass fraction 0.939.

Engine Model: Star 48B l. Manufacturer Name: TE-M-711-18. Designer: Thiokol. Gross Mass: 2,141 kg (4,720 lb). Empty Mass: 131 kg (288 lb). Propellants: Solid. Isp: 292 sec. Diameter: 1.24 m (4.08 ft). Chambers: 1. Country: USA. Status: In Production. Flown: 29.

Lengthened version of Star 48B to provide increased payload capability. The design incorporates a longer cylindrical section in the motor case. Total impulse 591,142 kgf-sec. Motor propellant mass fraction 0.939.

Engine Model: Star 48B s. Manufacturer Name: TE-M-711-17. Other Designations: 87.2-KS-17,335. Designer: Thiokol. Gross Mass: 2,134 kg (4,704 lb). Empty Mass: 124 kg (273 lb). Propellants: Solid. Thrust(vac): 77.109 kN (17,335 lbf). Isp: 286 sec. Burn time: 87 sec. Diameter: 1.24 m (4.08 ft). Chambers: 1. Country: USA. Status: In Production.

Short nozzle upper-stage motor is qualified for the McDonnell Douglas Payload Assist Module (PAM) Space Transportation System (STS). The basic version for STS missions contains 4430 pounds of propellant (an increase of 25 pounds over STAR 48) and has the same 72-inch overall length as the STS version of the STAR 48. The design incorporates the same high-energy propellant and high-strength case as the STAR 48. The semi-submerged nozzle uses a carbon-phenolic exit cone. Total impulse 578,461 kgf-s. Propellant mass fraction 0.942.

Engine Model: Star 48V. Manufacturer Name: TE-M-940-1. Designer: Thiokol. Propellants: Solid. Chambers: 1. Country: USA. Status: In Production.

Developed for Conestoga's upper stage, providing some ±4 degrees capability at 30 degree/sec using the same loaded casing as the 48B.. First Flight: 1994.

Star 48 used on Rocket Stages
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© Mark Wade, 1997 - 2008 except where otherwise noted.