Thermal integration of satellite vehicles with the Titan/Centaur, a cryogenic upper stage vehicle

Details Thermal integration of satellite vehicles with the Titan/Centaur, a cryogenic upper stage vehicle Thermal integration of satellite vehicles with the Titan/Centaur, a cryogenic upper stage vehicle

Jun 1989

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1989thph.confr....p&link_type=abstract

AIAA, Thermophysics Conference, 24th, Buffalo, NY, June 12-14, 1989. 9 p.

Physics

Cryogenic Rocket Propellants, Satellite Temperature, Thermal Analysis, Titan Centaur Launch Vehicle, Upper Stage Rocket Engines, Free Molecular Flow, Heat Transfer, Liquid Hydrogen, Temperature Distribution

Scientific paper

Titan/Centaur, a cryogenic upper stage now under development for use with the Titan IV launch vehicle, provides the attachment interface for payloads to be launched into geosynchronous orbit and other missions. Thermal requirements must be satisfied on both sides of the attachment interface. This paper describes the process of thermally integrating payloads with Centaur, typical problems encountered in this process, methods used to analyze the Centaur side of the interface, and development of thermal designs to meet requirements on both sides of the interface. All thermal integration problems encountered to date either have been resolved or are being analyzed to optimize resolution.

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