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Star 48B s

Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9 A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z Star 48B s Part of Star 48 Star-48B Short Credit: Thiokol Thiokol solid rocket engine. In Production. Short nozzle upper-stage motor qualified for the McDonnell Douglas Payload Assist Module (PAM) Space Transportation System (STS). AKA: 87.2-KS-17,335;TE-M-711-17. Status: In Production. Thrust: 77.11 kN (17,335 lbf). Gross mass: 2,134 kg (4,704 lb). Unfuelled mass: 124 kg (273 lb). Specific impulse: 286 s. Burn time: 87 s. Diameter: 1.24 m (4.08 ft). 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. Country: USA. Propellants: Solid. Agency: Thiokol. Bibliography: 410. Back to top of page Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9 A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z © 1997-2019 Mark Wade - Contact © / Conditions for Use

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