H-2-0
Engine · Japan
Original archive entry. The text, images and links below are kept as they were written.
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.
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.