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A Twin Gyro Attitude Control System Designed for Disturbance Instrumentation of a Space Vehicle
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English
Abstract
This paper summarizes the main considerations in applying a Twin Gyro Controller and the problems in implementing such a controller. Several Twin Gyro Controllers have been built for the purpose of measuring disturbances on a space vehicle, and the construction problems encountered are reported.
The main problem areas encountered involved alignment torquing provisions and mechanical tolerances. The three-axis Twin Gyro Controller was spun up to synchronous speed before launch and, as a result, the spinning of the spin stabilized vehicle introduced additional loads on the gyro wheels and torquers. These loads resulted in the use of a spiroid gear drive in the gyro torquer closed loop.
Considerations in applying the Twin Gyro Controller as an attitude controller and as a measurement device are covered in terms of sensitivity, accuracy, and limitations.
Authors
Citation
Stanfield, W., "A Twin Gyro Attitude Control System Designed for Disturbance Instrumentation of a Space Vehicle," SAE Technical Paper 640221, 1964, https://doi.org/10.4271/640221.Also In
References
- Sellers, D. F. “Fundamental Principles of Twin-Gyro Controller.” IRE Northeast Electronics Research and Engineering Meeting November 1960
- “High Moment Producing Techniques for Attitude Control and Stabilization of Manned Space Vehicles.” I February 1963
- Amster, M. N. Anderson, R. P. Williams, H. M. “Analysis of Twin-Gyro Attitude Controller.” Chance Vought Aircraft, Inc. June 16 1960
- Lopes, A. E. Ratcliff, J. W. Haville, J. R. “Results of Studies on a Twin-Gyro Attitude Control System for Space Vehicles.” AIAA Guidance and Controls Conference Aug. 12 1963