University Nanosat System Thermal Design, Analysis, and Testing

Abstract

Thermal design for space systems is an iterative process that balances the temperature requirements for all mission phases with the available resources. Secondary payloads often have to be designed for a wide range of conditions available on various launch platforms, without the benefit of additional resources such as power or thermal shielding. This paper will discuss the thermal design, analysis, and thermal vacuum testing of a small satellite payload that was initially intended for launch from the U.S. Space Shuttle and eventually launched on the EELV Heavy demonstration in December 2004.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 2006
Accession Number
ADA451038

Entities

People

  • Charlotte Gerhart

Organizations

  • Air Force Research Laboratory

Tags

DTIC Thesaurus Topics

  • Air Force Research Laboratories
  • Artificial Satellites
  • Energy
  • Launch Vehicles
  • Materials
  • Payload
  • Platforms
  • Small Satellites
  • Space Objects
  • Space Shuttles
  • Space Stations
  • Space Systems
  • Spacecraft
  • Thermal Analysis
  • Thermal Conductivity
  • Universities
  • Vehicles

Fields of Study

  • Physics

Readers

  • Electrical Engineering
  • Missile Defense Systems.
  • Systems Analysis and Design

Technology Areas

  • Space
  • Space - Satellites