This page no longer updated from 31 October 2001. Latest version can be found at 8D423

Government Designation: 8D423. Designer: Izotov. Application: UR-100 stage 2. Used on stages: UR-100 Stage 2. Used on launch vehicles: UR-100. Used on spacecraft: LK-700. Propellants: N2O4/UDMH Thrust(vac): 13,404 kgf. Thrust(vac): 131.00 kN. Isp: 325 sec. Burn time: 184 sec. Chambers: 1. Country: Russia. Status: Out of Production. References: 293 . Comments: Single chamber engine for UR-100 stage 2. Gas generator cycle with two large turbine exhaust pipes. Photos available in Russian Arms Cat. (Gives thrust as 15,200 kgf, Ispvac=326)).
Back to Index
Last update 12 March 2001.
Definitions of Technical Terms.
Contact Mark Wade with any corrections or comments.
Conditions for use of drawings, pictures, or other materials from this site..
© Mark Wade, 2001 .