HG-3 (original) (raw)

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

HG-3

Part of J-2

Advanced Engines

Advanced Engines
Advanced Engines planned for uprated Saturn and Nova boosters
Credit: © Mark Wade

Rocketdyne LOx/LH2 rocket engine. Study 1967. High-performance high-pressure chamber engine developed from J-2. Considered for upgrades to Saturn V launch vehicle upper stages. Technology led to Space Shuttle Main Engines.

Status: Study 1967. Thrust: 1,400.70 kN (314,890 lbf). Specific impulse: 451 s. Specific impulse sea level: 280 s. Burn time: 324 s. Height: 2.28 m (7.48 ft). Diameter: 2.03 m (6.66 ft).

Thrust (sl): 869.600 kN (195,494 lbf). Thrust (sl): 88,676 kgf.

Subtopics

HG-3-SL Rocketdyne LOx/LH2 rocket engine. Study 1966. High-performance high-pressure chamber engine developed from the J-2, fitted with lower-expansion nozzle for sea level use on Saturn INT-17. Technology led to Space Shuttle Main Engines.

Country: USA. Launch Vehicles: Saturn MLV-V-2, Saturn MLV-V-3, Saturn IB-B, Saturn V/4-260. Propellants: Lox/LH2. Stages: Saturn MS-IVB-2, Saturn MS-II-2. Agency: Rocketdyne.

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