Rotation elimination method and system for failed satellite

Abstract

The invention provides a rotation elimination method and system for a failed satellite. The method comprises the following steps: based on a rigid body attitude dynamic model, analyzing a variation rule of THE angular velocity and rotational kinetic energy of a rigid body under the action of a given external torque, and determining a control strategy of a first rotation elimination stage and a control strategy of a second rotation elimination stage; executing the control strategy of the first rotation elimination stage and measuring the angular velocity of a target failed satellite; executingthe control strategy of the second rotation elimination stage until the angular velocity of the target failed satellite satisfies the end condition of the second rotation elimination stage if it is judged that the angular velocity component satisfies the end condition of the first rotation elimination stage stage; the control strategy is used for applying a control torque to a given inertial spindle of the target failed satellite to reduce the angular velocity of the target failed satellite to a preset threshold. The method can ensure stable rotation elimination of the spacecraft under the condition that the control torque is limited and the measurement is inaccurate, the control scheme is simple and the practicability is strong.

Description

technical field [0001] The present invention relates to the field of space technology, and more specifically, to a derotation control method and system for a failed satellite. Background technique [0002] Failed satellites generally spin at high speed around their maximum inertial axis. Derotation of out-of-control satellites can turn them into stable or low-speed rotating targets. Derotation of failed satellites is an important space technology. On-orbit debris removal, orbital target Aspects such as capture play a vital role. In the actual derotation process, there will always be errors due to factors such as inaccurate angular velocity measurement and delay in control. These errors pose severe challenges to traditional measurement and control systems. [0003] The current satellite derotation control methods include the following: 1) damping derotation control method, which uses the method of increasing the target rotation damping or timing input damping dynamic torque...

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Problems solved by technology

[0004] In the ordinary damping derotation control method, the actuator needs to contact the target multiple times or continuously to realize the derotation control. If the actuator is misoperated, it will easily cause danger to the mission star; the linear feedback control method is not suitable for large angular velocity deviations. However, the calculation process of the nonlinear feedback control method is complex and has higher requirements on the measurement and control system; in the anti-rotation control scheme of "damping + feedback", the dynamic equation of rigid body attitude under the condition of external torque is not resolved Therefore, the simulated torque application law needs to be solved by numerical methods, the control process is complicated, and the practicability is low

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