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Thermal elastic shock and its effect on TOPEX spacecraft attitude controlThermal elastic shock (TES) is a twice per orbit impulsive disturbance torque experienced by low-Earth orbiting spacecraft. The fundamental equations used to model the TES disturbance torque for typical spacecraft appendages (e.g., solar arrays and antenna booms) are derived in detail. In particular, the attitude-pointing performance of the TOPEX spacecraft, when subjected to the TES disturbance, is analyzed using a three-axis nonlinear time-domain simulation. Results indicate that the TOPEX spacecraft could exceed its roll-axis attitude-control requirement during penumbral transitions, and remain in violation for approximately 150 sec each orbit until the umbra collapses. A localized active-control system is proposed as a solution to minimize and/or eliminate the degrading effects of the TES disturbance.
Document ID
19930031599
Document Type
Conference Paper
Authors
Zimbelman, Darrell F. (Fairchild Space & Defense Corp. Germantown, MD, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1991
Publication Information
Publication: In: Guidance and control 1991; Proceedings of the Annual Rocky Mountain Guidance and Control Conference, Keystone, CO, Feb. 2-6, 1991 (A93-15576 03-12)
Subject Category
SPACECRAFT DESIGN, TESTING AND PERFORMANCE
Report/Patent Number
AAS PAPER 91-056
Distribution Limits
Public
Copyright
Other