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Spacecraft Solar Array Deployment Analysis: A Probabilistic Approach
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English
Abstract
The mission objective of the TRW satellite requires four solar arrays be deployed simultaneously following separation from the inertial upper stage (IUS) booster. Due to the mechanical system's tolerances, the mass properties control procedure, and in-orbit temperature variation, as well as the potential for satellite tumbling, the possibility of sequential latch-up of flexible solar arrays becomes realistic. To determine the influence of sequential solar array latching on the deployment loads is, therefore, of great practical importance. Although the problem should be treated as a nonstationary stochastic process, the difficulty in obtaining an exact solution renders the process unsuitable. In response, this paper presents a Monte Carlo method for approximating a solution to such a problem.
Authors
Citation
Simonian, S. and Lee, W., "Spacecraft Solar Array Deployment Analysis: A Probabilistic Approach," SAE Technical Paper 841583, 1984, https://doi.org/10.4271/841583.Also In
References
- Likins P. W. “Dynamic Analysis of a System of Hinge-Connected Rigid Bodies with Nonrigid Appendages,” Technical Report 32-1576 JPL Pasadena, California February 1 1974
- Hurty W. C. Rubinstein M. F. Dynamics of Structures Prentice-Hall, Inc. Englewood Cliffs, New Jersey 1964