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针对航天器终端接近问题,解决了追踪航天器在跟踪到达期望目标点的过程中不与目标航天器发生碰撞的难题。首先,在目标航天器轨道系下建立了航天器的相对运动和避碰模型。其次,考虑外界扰动上界已知和未知两种情形,均给出了有限时间避碰控制器,且所设计的控制器都具有输入饱和特性。最后,应用Lyapunov稳定性理论证明了在所提出的控制器作用下系统是有限时间收敛的,并且,利用避碰势函数证明了所设计的控制器能够实现避碰。仿真结果表明,所提出的控制器是有效的。
Aiming at the approaching problem of the spacecraft terminal, the problem that the tracking spacecraft does not collide with the target spacecraft during the tracking of the desired target point is solved. First, the spacecraft’s relative motion and collision avoidance model are established under the target spacecraft orbital system. Second, given the known and unknown upper bounds of disturbance, both finite time avoidance controllers are given, and the designed controllers have input saturation characteristics. Finally, the Lyapunov stability theory is used to prove that the system converges to a finite time under the proposed controller. Moreover, the collision avoidance potential function is used to prove that the designed controller can avoid collision. Simulation results show that the proposed controller is effective.