The Space Transportation System uses reaction control systems for achieving required attitudes. The Primary Reaction Control System has 38 thrasters, each with 870 lbs. thrust. They provide the Orbiter will all axis control of translation and rotation. Finer control is provided by the Vernier Reaction Control System. The URCS has 6 thrusters, each providing 24 lbs. of thrust. This limits the translation capability of the Orbiter in the URCS mode because there are no forward nor aft pointing thrusters, but provides attitude control capability to an accuracy of plus or minus .01 degrees deadband, and a limit cycle rate of .02 degress per second. Disturbinb forces fall into four categories: 1) Movement of equipment of crewmembers, 2) Unbalanced ejection of mass, 3) Aerodynamic drag, 4) Gravity gradient forces. The first two can be controlled procedurally; the third and foarth cannot. A control moment gyro (CMG) package would endow the Orbiter with a very accurate pointing capability which does not require use of the RCS. Many projects which are developing their own precision pointing systems could well dispense with then.
Control moment gyros for the space shuttle
Momentensteuerkreisel fuer das Space Shuttle
1984
3 Seiten, 4 Quellen
Aufsatz (Konferenz)
Englisch
Control Moment Gyros as Space-Robotics Actuators
AIAA | 2008
|Control Moment Gyros as Space-Robotics Actuators
British Library Conference Proceedings | 2008
|Adaptive control of space station with control moment gyros
Tema Archiv | 1992
|Control moment gyros in attitude control
Engineering Index Backfile | 1966
|Control moment gyros in attitude control.
AIAA | 1966
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