LK-1 engine
Engine · Israel
Original archive entry. The text, images and links below are kept as they were written.
IAI solid rocket engine. In production. Lengthened version of Shavit rocket motor. Lower stage used 9:1 nozzle. 23.6:1 nozzle for upper stage use increased Isp to 279 seconds, First flight 1995. Solid propellant rocket stage. Lengthened version of Shavit/RSA-3 rocket motor. For lower stage use with 17.1:1 nozzle. Fitted with 23.6:1 nozzle for upper stage use specific impulse increases to 279 seconds, length to 8.4 m, and empty and gross mass are increased by 135 kg.
Fitted with 23.6:1 nozzle for upper stage use length was 8.4 m, and empty and gross mass were increased by 135 kg.
Area Ratio: 9. Propellant Formulation: HTPB.
Related
- Country
- Israel
- Launch Vehicles
- Shaviyt 1, LeoLink LK-1, LeoLink LK-2
- Propellants
- Solid
- Stages
- LK-1 engine
- Agency
- IAI