SRM-1

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SRM-1

IUS
Credit: NASA

CSD solid rocket engine. Used in TOS; IUS-1 on Shuttle, Titan 34D. Known by manufacturer as Orbus 21. Propellant: 86% solids made up of HTPB UTP-19360A. Shape: cylindrical. First flight 1982. Solid propellant rocket stage. IUS-2 stage with simplified electronics.

AKA: ESBM;IUS-1;Orbus 21;TOS. Status: Retired 2004. Number: 84 . Thrust: 181.50 kN (40,803 lbf). Gross mass: 10,841 kg (23,900 lb). Unfuelled mass: 1,134 kg (2,500 lb). Specific impulse: 296 s. Specific impulse sea level: 115 s. Burn time: 152 s. Height: 3.15 m (10.33 ft). Diameter: 2.34 m (7.67 ft).

Thrust (sl): 70.500 kN (15,849 lbf). Thrust (sl): 7,191 kgf. Chamber Pressure: 58.00 bar. Area Ratio: 64. Propellant Formulation: HTPB.

Country: USA. Launch Vehicles: Titan 34D/IUS, Titan 34D, Titan 402A/IUS, Commercial Titan 3, Titan 405A, Athena-1, Titan 402B/IUS, Athena-2, Athena-3. Propellants: Solid. Stages: SRM-1. Agency: CSD.

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