Thermally Induced Attitude Disturbance Control for Spacecraft with a Flexible Boom-Reference-Cited by-同舟云学术

Thermally Induced Attitude Disturbance Control for Spacecraft with a Flexible Boom

Published:2002-03 Issue:2 Volume:39 Page:325-328
ISSN:0022-4650
Container-title:Journal of Spacecraft and Rockets
language:en
Short-container-title:Journal of Spacecraft and Rockets

Author:

Park Sang-Young¹

Affiliation:

1. Naval Postgraduate School, Monterey, California 93943

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Space and Planetary Science,Aerospace Engineering

Link

https://arc.aiaa.org/doi/pdf/10.2514/2.3816

Reference7 articles.

1. Thermally Induced Attitude Dynamics of a Spacecraft with a Flexible Appendage

2. Mathematical Models of Flexible Structures

3. Kwon, Y. W., and Bang, H., The Finite Element Method Using Matlab, CRC Mechanical Engineering Series, CRC Press, Washington, DC, 1997, pp.393-482.

4. Schmidt, S. P. “Active Vibration Control of Flexible Structures Using the Modular Control Patch (MCP),” M.S. Thesis,Dept. of Aeronautics and Astronautics, Naval PostgraduateSchool, Monterey, CA,March 1997.

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