DESCENT TRAJECTORIES FOR MANNED SPACE VEHICLES,

Abstract

The problem of designing a manned space vehicle which must survive entry into the earth's atmosphere is discussed from the systems point of view. In the design of such a vehicle peak deceleration loads become an important consideration. This aspect of the problem together with the aerodynamic heating and landing point dispersion factors is considered for two classes of re-entry bodies: (1) returning low-altitude satellite, and (2) vehicles which re-entry at or near escape velocity such as circumlunar vehicles. Finally, the heat shielding problem is presented in detail along with some solutions. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jun 20, 1958
Accession Number
AD0605929

Entities

People

  • R. L. Phillips

Organizations

  • TRW Inc.

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Aerodynamic Heating
  • Altitude
  • Artificial Satellites
  • Descent Trajectories
  • Escape Velocity
  • Heat Energy
  • Low Altitude
  • Orbits
  • Spacecraft
  • Trajectories
  • Vehicles

Readers

  • Space Exploration and Orbital Mechanics.
  • Systems Analysis and Design

Technology Areas

  • Space
  • Space - Orbital Debris
  • Space - Spacecraft Maneuvers