Ablative Thermal Protection Structure Design of Ballistic Reentry Spacecraft,

Abstract

The paper presents the ablative thermal protection structure design of a ballistic reentry spacecraft. The concepts, material selection, design approach, analytical computation and evaluation are described. Thermal protection structure, ablative material, ballistic reentry spacecraft and design.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1992
Accession Number
ADA256908

Entities

People

  • Chen Qinghua

Organizations

  • National Air and Space Intelligence Center

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Ablation
  • Ablative Materials
  • Adhesives
  • Coefficients
  • Composite Materials
  • Decomposition
  • Flux Density
  • Heat Energy
  • Insulation
  • Low Temperature
  • Materials
  • Reentry Vehicles
  • Spacecraft
  • Thermal Analysis
  • Thermal Efficiency
  • Thermal Properties
  • Thermodynamics

Fields of Study

  • Physics

Readers

  • Reinforced Composite Materials
  • Software Engineering

Technology Areas

  • Space
  • Space - Hall-Effect Thruster
  • Space - Orbital Debris