Tests of an attitude control system, using skewed reaction wheels and a spaceborne microcomputer, are described. Stability, accuracy, and speed of response were evaluated in the normal and backup modes, mode transitions, various submodes, and during wheel failure; tests were supported by analyses and computer simulations. For system operation with the minimum of three wheels, peak attitude errors are acceptable even for a maximum motor-torque failure. The importance of feeding the momentum of a failed wheel into the distribution matrix is proven. It is shown that momentum control, in contrast to traditional torque control, offers many advantages in the design and operation. A skewed reaction wheel system appears attractive for high accuracy and reliability in geostationary communications satellites.
Air bearing testing of a skewed reaction wheel system for attitude control
Luftlager-Pruefung eines abgeschraegten Reaktionsrad-Systems zur Fluglagenregelung
Comsat Technical Review ; 9 , 1 ; 157-202
1979
46 Seiten, 6 Quellen
Article (Journal)
English
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