Abstract
Sensor-based Optimal Attitude Reorientation Control Scheme Based on Computational Programming Approach
Highlights
Many current and future spacecraft have mission requirements of pointing, tracking, and multitarget acquisition within the physical limits of actuators
In this paper, we extend the concept in Refs. 21 and 22 to solve the optimal large-angle reorientation attitude control (OLRAC) problem of a rigid spacecraft with an open time of maneuver that is actuated by K > 3 reaction wheels mounted in arbitrary and linearly independent orientations
We presented a novel method to solve the OLRAC problem of a rigid asymmetric spacecraft actuated by K reaction wheels mounted in arbitrary orientations with respect to the spacecraft frame
Summary
Many current and future spacecraft have mission requirements of pointing, tracking, and multitarget acquisition within the physical limits of actuators. To achieve these tasks, sequences of revolutions about body principal axes are required to generate the required attitude reorientation maneuver. During the spacecraft attitude maneuver, the directional vectors of bright celestial objects, such as the Sun and the Earth, are measured by optical sensors (e.g., infrared sensors or star sensors). Many studies considering a rigid spacecraft with three attached control torques perpendicular to the three principal axes have been published, including studies on time-optimal attitude control,(1,2) energy-optimal control,(3) feedback control with input saturation,(4) finite-time output feedback control,(5) adaptive sliding mode control,(6–10) and path-planning control.(11,12)
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