Thermal design of the IMP-I and H spacecraftA description of the thermal subsystem of the IMP-I and H spacecraft is presented. These two spacecraft were of a larger and more advanced type in the Explorer series and were successfully launched in March 1971 and September 1972. The thermal requirements, analysis, and design of each spacecraft are described including several specific designs for individual experiments. Techniques for obtaining varying degrees of thermal isolation and contact are presented. The thermal control coatings including the spaceflight performance of silver-coated FEP Teflon are discussed. Predicted performance is compared to measured flight data. The good agreement between them verifies the validity of the thermal model and the selection of coatings.
Document ID
19740056381
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hoffman, R. H. (NASA Goddard Space Flight Center Thermophysics Branch, Greenbelt, Md., United States)
Date Acquired
August 7, 2013
Publication Date
July 1, 1974
Subject Category
Space Vehicles
Report/Patent Number
ASME PAPER 74-ENAS-32
Meeting Information
Meeting: Intersociety Conference on Environmental Systems