Convex Approach to Optimal Spacecraft Attitude Reorientation with Keep-Out Constraints

What is it about?

This paper suggests a new way to tackle the challenge of reorienting a spacecraft while considering specific constraints. By using a mix of optimization techniques, the complex control problem becomes more computationally tractable. The proposed method uses a mathematical representation called the Direction Cosine Matrix (DCM) to describe the spacecraft's orientation, allowing for handling constraints and dealing with partially known initial or final attitudes. The approach also ensures a smooth torque profile, which is crucial for practical applications when integrating with actual spacecraft actuators. The goal is to make spacecraft reorientation more efficient and feasible in real-world scenarios.

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