Department of Automation, School of Aerospace Engineering, Xiamen University, Xiamen 361102, China.
Math Biosci Eng. 2023 Jan 13;20(3):5921-5948. doi: 10.3934/mbe.2023256.
The high-accuracy attitude maneuvering problem for spacecraft systems is investigated. A prescribed performance function and a shifting function are first employed to ensure the predefined-time stability of attitude errors and eliminate the constraints on tracking errors at the incipient stage. Subsequently, a novel predefined-time control scheme is developed by combining prescribed performance control and backstepping control procedures. Radial basis function neural network and minimum learning parameter techniques are introduced to model the function of lumped uncertainty including inertial uncertainties, actuator faults and virtual control law derivatives. According to the rigorous stability analysis, the preset tracking precision can be achieved within a predefined time and the fixed-time boundedness of all closed-loop signals is established. Finally, the efficacy of the propounded control scheme is manifested through numerical simulation results.
研究了航天器系统的高精度姿态机动问题。首先采用规定性能函数和转移函数，以确保姿态误差的预定时间稳定性，并消除初始阶段跟踪误差的约束。随后，通过结合规定性能控制和反推控制过程，开发了一种新的预定时间控制方案。引入了径向基函数神经网络和最小学习参数技术来建模包括惯性不确定性、执行器故障和虚拟控制律导数在内的集中不确定性函数。根据严格的稳定性分析，可以在预定时间内实现预设跟踪精度，并建立所有闭环信号的固定时间有界性。最后，通过数值模拟结果表明了所提出的控制方案的有效性。
