AN INVESTIGATION OF CREW ESCAPE FROM VEHICLES PERFORMING AT SUPERORBITAL RE-ENTRY VELOCITIES

Abstract

Detailed results are presented from an investigation to determine the technical feasibility of providing crew escape capability for space vehicles during reentry at supercircular velocity. The general requirements for reentry corridor compatibility are discussed, and the NASA M-II and M-I configurations are selected for the Parent and Escape Vehicles, respectively. Detailed flight mechanics analyses are conducted; a guidance concept, which commands a rate of change of lift coefficient as a function of combinations of various trajectory parameters, is developed and evaluated. Aerothermodynamic analyses are conducted, and transient temperature responses, ablation and insulation weights, and overall heat shield weights at various body locations on the escape vehicle are given. The other basic escape vehicle subsystems are investigated to determine weight and volume requirements, electrical power requirements, cooling requirements, and other design parameters. (Author)

Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1964
Accession Number
AD0355783

Entities

People

  • J. E. Hofferberth

Tags

DTIC Thesaurus Topics

  • Ablation
  • Coefficients
  • Cooling
  • Guidance
  • Heat Shields
  • Insulation
  • Mechanics
  • Orbits
  • Spacecraft
  • Spacecraft Orbits
  • Thermal Insulation
  • Trajectories
  • Vehicles

Fields of Study

  • Engineering

Readers

  • Aviation Science / Aeronautics.
  • Software Engineering
  • Space Exploration and Orbital Mechanics.

Technology Areas

  • Microelectronics
  • Microelectronics - Microelectromechanical Systems
  • Space
  • Space - Hall-Effect Thruster
  • Space - Spacecraft Maneuvers