Orbit-to-Orbit Shuttle Engine Design Study. Book 1. Parametric Cycle Study

Abstract

This report presents the analytical design of propulsion systems utilizing LOX/Hydrogen propellants to be used as the propulsion for the Orbit to Orbit Space Vehicle of 65,000 lb lift-off weight. The report contains the evaluation of various engine cycles in the thrust range of 8,000 lb to 50,000 lb thrust for performance, weight and envelope culminating in the cycle selection and detail design of a 25,000 lb and 10,000 lb thrust engine. The engine concepts are described in sufficient detail to obtain reliable engine weight, performance, envelope information and methods of engine control. The impact of various engine design requirements were evaluated. The engines are designed to be reusable and capable of starting in the idle mode operation. The technology requirements for meeting the engine design and operating requirements are identified.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1972
Accession Number
AD0900190

Entities

People

  • Werner P. Luscher

Organizations

  • Aerojet Rocketdyne Holdings

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Combustion
  • Computer Programs
  • Failure Mode And Effect Analysis
  • Fuel Pumps
  • Heat Transfer
  • High Pressure
  • Liquid Hydrogen
  • Liquid Oxygen
  • Materials
  • Plastic Explosives
  • Propellants
  • Propulsion Systems
  • Spacecraft
  • Temperature Gradients
  • Test And Evaluation
  • Thrust Chambers
  • Vehicles

Readers

  • Aerospace Engineering
  • Missile Defense Systems.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster