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Space Station Control Moment Gyroscope Lessons LearnedFour 4760 Nms (3510 ft-lbf-s) Double Gimbal Control Moment Gyroscopes (DGCMG) with unlimited gimbal freedom about each axis were adopted by the International Space Station (ISS) Program as the non-propulsive solution for continuous attitude control. These CMGs with a life expectancy of approximately 10 years contain a flywheel spinning at 691 rad/s (6600 rpm) and can produce an output torque of 258 Nm (190 ft-lbf)1. One CMG unexpectedly failed after approximately 1.3 years and one developed anomalous behavior after approximately six years. Both units were returned to earth for failure investigation. This paper describes the Space Station Double Gimbal Control Moment Gyroscope design, on-orbit telemetry signatures and a summary of the results of both failure investigations. The lessons learned from these combined sources have lead to improvements in the design that will provide CMGs with greater reliability to assure the success of the Space Station. These lessons learned and design improvements are not only applicable to CMGs but can be applied to spacecraft mechanisms in general.
Document ID
20100021932
Document Type
Conference Paper
Authors
Gurrisi, Charles (L-3 Communications Corp. Budd Lake, NJ, United States)
Seidel, Raymond (L-3 Communications Corp. Budd Lake, NJ, United States)
Dickerson, Scott (L-3 Communications Corp. Budd Lake, NJ, United States)
Didziulis, Stephen (Aerospace Corp. El Segundo, CA, United States)
Frantz, Peter (Aerospace Corp. El Segundo, CA, United States)
Ferguson, Kevin (Boeing Co. Houston, TX, United States)
Date Acquired
August 29, 2013
Publication Date
May 12, 2010
Publication Information
Publication: Proceedings of the 40th Aerospace Mechanisms Symposium
Subject Category
Space Sciences (General)
Distribution Limits
Public
Copyright
Public Use Permitted.

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IDRelationTitle20100021914Analytic PrimaryProceedings of the 40th Aerospace Mechanisms Symposium