Accession Number:

ADA277519

Title:

7.5K 1bf Thrust Engine Preliminary Design for Orbit Transfer Vehicle. Task D.5

Descriptive Note:

Final rept.

Corporate Author:

AEROJET PROPULSION DIV SACRAMENTO CA

Report Date:

1994-01-01

Pagination or Media Count:

365.0

Abstract:

This document summarizes the preliminary design of the Aerojet version of the Orbit Transfer Vehicle main engine. The concept of a 7500 lbf thrust L02GH2 engine using the dual expander cycle for optimum efficiency is validated through power balance and thermal calculations. The engine is capable of 101 throttling from a nominal 2000 psia to a 200 psia chamber pressure. Reservations are detailed on the feasibility of a tank head start, but the design incorporates low speed turbopumps to mitigate the problem. The mechanically separate high speed turbopumps use hydrostatic bearings to meet engine life requirements, and operate at sub-critical speed for better throttling ability. All components were successfully packaged in the restricted envelope set by the clearances for the extendibleretractable nozzle. Gimbal design uses an innovative primary and engine out gimbal system to meet the -20 deg gimbal requirement. The hydrogen regenerator and LOXGH2 heat exchanger uses the Aerojet platelet structures approach for a highly compact component design. The extendibleretractable nozzle assembly uses an electric motor driven jack- screw design and a one segment carbon-carbon or silicide coated columbium nozzle with an area ratio, when extended, of 14301. A reliability analysis and risk assessment concludes the report. Rocket engine, Cryogenic propellants, Lunar mission, Cryogenic turbopumps, Throttling engine, Health monitor systems.

Subject Categories:

  • Rocket Engines
  • Rocket Propellants
  • Spacecraft Trajectories and Reentry

Distribution Statement:

APPROVED FOR PUBLIC RELEASE