A concept is described of a three axis attitude control of a satellite for operators of satellite tracking and for beginners of a satellite attitude control design. For an easier understanding of the basic concept of the attitude control of BS-2b (Broadcasting Satellite-2b) and other satellites, the answers to the following questions are examined: (1) What are the characteristics of a three axis attitude controlled satellite on a synchronized orbit; (2) What is the purpose of a satellite attitude control; (3) What kinds of disturbance exist on satellite orbits; (4) How do they affect satellites; (5) Why is wheel-control important; (6) What kinds of satellite rotation sensors exist, and what are their limitations; (7) What is the difference between zero-momentum method and bias-momentum method; (8) What are actuators that control various disturbances, and what are their characteristics; (9) What is a concept of automatic control as a guide for understanding satellite attitude control system; and (10) What is a conceptual drawing of an altitude control system. The above-mentioned items are not enough, because the operations of the attitude control systems of various types of satellites are individually different and complicated. Therefore, the attitude control systems of BS-2b, MOS-1 (Marine Observation Satellite-1) and ETS-5 (Engineering Test Satellite-5) are shown as examples.
Three Axis Attitude Control of a Satellite
1988
220 pages
Report
No indication
English
Unmanned Spacecraft , Manned Spacecraft , Astronautics , Attitude stability , Control systems design , Satellite attitude control , Synchronous satellites , Three axis stabilization , Feedback control , Actuators , Angular momentum , Attitude gyros , Japanese spacecraft , Satellite tracking , Solar sensors , Spacecraft stability , Foreign technology
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