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Star 48B

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 Part of Star 48 Thiokol solid rocket engine. In Production. Long nozzle upper-stage motor qualified for the McDonnell Payload Assist Module (PAM) Delta. AKA: 87.2-KS-17,735;TE-M-799. Status: In Production. Thrust: 66.00 kN (14,837 lbf). Gross mass: 2,137 kg (4,711 lb). Unfuelled mass: 126 kg (277 lb). Specific impulse: 286 s. Burn time: 87 s. Height: 2.03 m (6.67 ft). Diameter: 1.25 m (4.08 ft). 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. Propellant Formulation: HTPB. Country: USA. Propellants: Solid. Agency: Thiokol. 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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