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首页> 外文期刊>Journal of aerospace engineering >Attitude Coordination Control for Formation Flying Spacecraft Based on the Rotation Matrix
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Attitude Coordination Control for Formation Flying Spacecraft Based on the Rotation Matrix

机译：基于旋转矩阵的编队飞行器姿态协调控制

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摘要

Two attitude coordination controllers that make the system converge to the equilibrium point in finite time are designed for spacecraft formation flying with actuator saturation constraints. The first finite-time attitude coordination controller is suitable for the situation that all states of the closed-loop system are available. To deal with the problem of failing to measure angular velocity, a novel filter is presented in the second finite-time attitude coordination controller. Because the model of spacecraft formation flying is established based on the rotation matrix, the closed-loop system does not have the drawback of unwinding. The theoretical analysis and simulation results are given to prove the validity of the proposed controllers. (C) 2017 American Society of Civil Engineers.
机译：设计了两个使系统在有限时间内收敛到平衡点的姿态协调控制器，用于具有执行器饱和约束的航天器编队飞行。第一个有限时间姿态协调控制器适用于闭环系统所有状态均可用的情况。为了解决无法测量角速度的问题，在第二个有限时间姿态协调控制器中提出了一种新颖的滤波器。由于基于旋转矩阵建立了航天器编队飞行模型，因此闭环系统不存在退绕的缺点。通过理论分析和仿真结果验证了所提控制器的有效性。 （C）2017年美国土木工程师学会。

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