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Spacecraft attitude determination and control
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<p>Spacecraft attitude control is the process of controlling the orientation of a <a href="/facts/Spacecraft/YQqQaUw0">spacecraft</a> (vehicle or satellite) with respect to an <a href="/facts/Inertial_frame_of_reference/1U6TrdG3">inertial frame of reference</a> or another entity such as the <a href="/facts/Celestial_sphere/TYAtXgor">celestial sphere</a>, certain fields, and nearby objects, etc. </p><p>Controlling vehicle attitude requires <a href="/facts/Actuators/mF9qVJJR">actuators</a> to apply the torques needed to orient the vehicle to a desired attitude, and <a href="/facts/Algorithms/fnl5NmRt">algorithms</a> to command the actuators based on the current attitude and specification of a desired attitude. </p><p>Before and during attitude control can be performed, spacecraft attitude determination must be performed, which requires <a href="/facts/Sensor/RN8SXbjs">sensors</a> for absolute or relative measurement. </p><p>The broader integrated field that studies the combination of sensors, actuators and algorithms is called <i><a href="/facts/Guidance,_navigation_and_control/Terngs4t">guidance, navigation and control</a></i>, which also involves non-attitude concepts, such as <a href="/facts/Position_determination/yY41HfWV">position determination</a> and <a href="/facts/Navigation/sGGAJ0AQ">navigation</a>. </p>