DESIGN STUDY OF A LARGE UNCONVENTIONAL LIQUID PROPELLANT ROCKET ENGINE AND VEHICLE. VOLUME 5. ADVANCED ENGINE-VEHICLE INTEGRATION STUDY

Abstract

Identifiers: F-D engines, Thrust vector control, Weight, Bell nozzles.Advanced engine design concepts were studied on the cost performance parameter (dollars per pound of payload) of a total airborne vehicle and ground support system. Emphasis was placed on use of a 2 million pounds sea level force deflection (F-D) engine. This engine was used in two basic vehicle configurations: a two stage vehicle with a thrust to weight ratio (T/W) of 1.1 and using the F-D engine in both stages operating at Pc of 1000 psi; and a single-stage-to-orbit vehicle with a T/W of 1.4 and using one F-D engine operating at Pc of 3000 psi. Emphasis was placed on the engine installation, the engine influence on connecting subsystems, and the engine mounting structure.

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Document Details

Document Type
Technical Report
Publication Date
Apr 18, 1962
Accession Number
AD0328952

Entities

Organizations

  • Aerojet Rocketdyne Holdings

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aircrafts
  • Airframes
  • Altitude
  • Bell Nozzles
  • Design Criteria
  • Fuel Tanks
  • Ground Support
  • Liquid Hydrogen
  • Liquid Oxygen
  • Liquid Propellant Rocket Engines
  • Liquid Propellants
  • Materials Processing
  • Payload
  • Pressurization
  • Propellant Tanks
  • Propellants
  • Sea Level

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Missile Defense Systems.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster