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Precision Attitude Control of Symmetric Spinning Bodies

Report Number: AFAL TR 71-224
Author: Lorell, Kenneth R.
Author: Lange, Benjamin
Corporate Author: Stanford University Department of Aeronautics and Astronautics
Laboratory: Air Force Avionics Laboratory
Date of Publication: 1971-04
Pages: 152
Contract: F33615-67-C-1245
Project: 5102
Task: 510215
AD Number: AD0730854

Motivated by the arc-second pointing requirement of the Unsupported Gyroscope experiment and other satellite applications, this research investigates the problems associated with the precision attitude control of symmetric spinning bodies. An attitude control system is synthesized and then is studied by analog simulation. Controller performance and limitations are evaluated, using a laboratory model called the Spinning Vehicle Simulator (SVS). A technique devised at Stanford University in 1966 that simplifies the design of spinning-vehicle attitude controllers is used to select controller gains. The resulting system, simulated on an analog computer, produces excellent response characteristics and is insensitive to vehicle parameter or gain changes. The magnitude of the attitude error is shown to have zero-frequency and spin-frequency components proportional to the magnitude of body-fixed and inertially fixed moments, respectively.

Lockheed Martin Missiles & Fire Control
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