A RetroSearch Logo

Home - News ( United States | United Kingdom | Italy | Germany ) - Football scores

Search Query:

Showing content from http://www.astronautix.com/c/../t/../s/srm-1.html below:

SRM-1


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 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. 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

RetroSearch is an open source project built by @garambo | Open a GitHub Issue

Search and Browse the WWW like it's 1997 | Search results from DuckDuckGo

HTML: 3.2 | Encoding: UTF-8 | Version: 0.7.4