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| Aircraft attitude ： ウィキペディア英語版 |
Attitude control
Attitude control is controlling the orientation of an object with respect to an inertial frame of reference or another entity (the celestial sphere, certain fields, nearby objects, etc.).
Controlling vehicle attitude requires ''sensors'' to measure vehicle orientation, ''actuators'' to apply the torques needed to re-orient the vehicle to a desired attitude, and ''algorithms ''to command the actuators based on (1) sensor measurements of the current attitude and (2) specification of a desired attitude. The integrated field that studies the combination of sensors, actuators and algorithms is called "Guidance, Navigation and Control" (GNC).
== Introduction ==
A spacecraft's attitude must typically be stabilized and controlled for a variety of reasons. It is oftentimes needed so that the spacecraft high-gain antenna may be accurately pointed to Earth for communications, so that onboard experiments may accomplish precise pointing for accurate collection and subsequent interpretation of data, so that the heating and cooling effects of sunlight and shadow may be used intelligently for thermal control, and also for guidance: short propulsive maneuvers must be executed in the right direction.
抄文引用元・出典: フリー百科事典『 ウィキペディア（Wikipedia）』
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