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Accession Number:
AD0607343
Title:
REACTION WHEEL ATTITUDE CONTROL SYSTEM,
Corporate Author:
TRW SPACE TECHNOLOGY LABS LOS ANGELES CALIF
Report Date:
1958-12-18
Abstract:
The disturbance torques acting upon a satellite or space vehicle are extremely small. In the absence of aerodynamic effects, these torques are on the order of 10 to the minus 4th power lb-ft or less. Therefore, only minute control torques are required to counteract any disturbance which might exist. Torques of this magnitude can be developed by a small a-c or d-c motor connected to a small flywheel. The flywheel is then accelerated according to the torque demands of the control system. Due to the fact that the motor has a maximum speed, for some missions the inertial wheel alone is insufficient for attitude control for any significant period of time. Some means of intermittently slowing down the inertial wheel is therefore necessary. This can be accomplished through the use of gas jets mounted on the vehicle. The purpose of the report is to present a brief description and simplified analysis of a single axis attitude control system using an inertial wheel. A three-axes control system including inter-axis coupling is currently under investigation. Author
Pages:
0005
File Size:
0.00MB
