Review of thermal design of ISIS `A' satellite (International Satellites for Ionospheric Studies); design conditions dictated by details of structure, orbit mission and `on board' temperature limits and payload power dissipation are considered which showed that `passive' thermal control of spacecraft was feasible; computer programmed multi-node heat balance analysis have been developed and used to predict spacecraft flight temperatures and evaluate design parameters; scope of thermal vacuum test program required to establish design integrity is outlined.
Thermal design of ISIS `A' spacecraft
Can Aeronatuics Space J
Canadian Aeronautics and Space Journal ; 12 , n 10 ; p 425-432
1966
8 pages
Aufsatz (Zeitschrift)
Englisch
© Metadata Copyright Elsevier B. V. All rights reserved.
Thermal design of the ISIS ''A'' spacecraft.
NTRS | 1966
|Isis-a Spacecraft Magnetic Tests
NTIS | 1969
|Isis-B Spacecraft Magnetic Tests
NTIS | 1972
|ISIS-B spacecraft magnetic tests
NTRS | 1972
|ISIS-A spacecraft magnetic tests
NTRS | 1969
|