High temperature superconducting infrared imaging satellite

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19940021207.pdf (1.25 MB)
Authors
Angus, B.
Covelli, J.
Davinic, N.
Hailey, J.
Jones, E.
Ortiz, V.
Racine, J.
Satterwhite, D.
Spriesterbach, T.
Sorensen, D.
Subjects
INFRARED DETECTORS
SATELLITE ATTITUDE CONTROL
SATELLITE DESIGN
SATELLITE OBSERVATION
INFRARED IMAGERY
SPACECRAFT COMMUNICATION
STRUCTURAL DESIGN
SUPERCONDUCTING DEVICES
TEMPERATURE CONTROL
THREE AXIS STABILIZATION
Advisors
Date of Issue
1992-01
Date
Jan 01, 1992
Publisher
Language
Abstract
A low earth orbiting platform for an infrared (IR) sensor payload is examined based on the requirements of a Naval Research Laboratory statement of work. The experiment payload is a 1.5-meter square by 0.5-meter high cubic structure equipped with the imaging system, radiators, and spacecraft mounting interface. The orbit is circular at 509 km (275 nmi) altitude and 70 deg. inclination. The spacecraft is three-axis stabilized with pointing accuracy of plus or minus 0.5 deg. in each axis. The experiment payload requires two 15-minute sensing periods over two contiguous orbit periods for 30 minutes of sensing time per day. The spacecraft design is presented for launch via a Delta 2 rocket. Subsystem designs include attitude control, propulsion, electric power, telemetry, tracking and command, thermal design, structure, and cost analysis.
Type
Conference Paper
Description
URI
https://hdl.handle.net/10945/60130
 https://ntrs.nasa.gov/search.jsp?R=19940021207
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Unspecified Center
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Citation
USRA, Proceedings of the 8th Annual Summer Conference: NASA(USRA Advanced Design Program; p. p 274-286
Distribution Statement
Approved for public release; distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.
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