H-2-0

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

H-2-0

Part of J-1

Nissan solid rocket engine. Used as strap-on booster on H-2, first stage on J-1. First flight 1994. Solid propellant rocket stage. Shorter monolithic motor using filament-wound case technology from Thiokol. Version for J-1 has 1,000 kg less propellant and 1,200 kg less empty mass than later H-2 SRB. J-1 first stage.

AKA: J-1-1. Status: In production. Number: 15 . Thrust: 1,540.00 kN (346,200 lbf). Gross mass: 70,400 kg (155,200 lb). Unfuelled mass: 11,250 kg (24,800 lb). Specific impulse: 273 s. Specific impulse sea level: 237 s. Burn time: 94 s. Height: 23.36 m (76.64 ft). Diameter: 1.81 m (5.93 ft).

Thrust (sl): 1,336.900 kN (300,547 lbf). Thrust (sl): 136,328 kgf. Chamber Pressure: 46.00 bar. Area Ratio: 10.

Subtopics

H-2/J-1-1 Nissan solid rocket engine. In Production. Used in J-1-1.

Country: Japan. Launch Vehicles: H-II, H-II (2S), J-1. Propellants: Solid. Stages: H-2-0. Agency: Nissan.

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