NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
The spacecraft structure and thermal design considerationsThis paper covers the general structural and thermal design considerations of the Telstar satellite. The basic objectives were to maintain the electronic components in a near room temperature environment and to protect the electronics packge from high-frequency vibration excitation. These objectives were realized by dividing satellite into two lumped masses, the shell and the centrally located electronics package, and by utilizing nylon lacing for support of the electronics package. The package was provided with an active temperature control, regulating radiative heat flow between the skin and the package. Results of on-the-ground experimental evaluation and of telemetry data are given.
Document ID
19640000968
Acquisition Source
Goddard Space Flight Center
Document Type
Contribution to a larger work
Authors
P. Hrycak
(Goddard Space Flight Center Greenbelt, Maryland, United States)
D. E. Koontz
(Goddard Space Flight Center Greenbelt, Maryland, United States)
C. Maggs
(Goddard Space Flight Center Greenbelt, Maryland, United States)
J. W. Stafford
(Goddard Space Flight Center Greenbelt, Maryland, United States)
B. A. Unger
(Goddard Space Flight Center Greenbelt, Maryland, United States)
A. M. Wittenberg
(Goddard Space Flight Center Greenbelt, Maryland, United States)
Date Acquired
August 2, 2013
Publication Date
July 1, 1963
Publication Information
Publication: The Bell System Technical Journal
Publisher: Nokia Bell Labs
Volume: 42
Issue: 4
Issue Publication Date: July 1, 1963
ISSN: 0005-8580
URL: https://ieeexplore.ieee.org/document/6779725
Subject Category
Space Sciences
Accession Number
64N10877
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
STRUCTURAL DESIGN
THERMAL PROTECTION
TELSTAR SATELLITE
No Preview Available