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Ascent control of heavy-lift launch vehicle with guaranteed predefined performance

机译：高升力发动机的上升控制，具有保证的预定义的性能

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In this paper, the problem of ascent attitude tracking control is studied for a heavy-lift launch vehicle (HLV) with guaranteed predefined performances. Firstly, the attitude tracking error dynamics model is developed by using a second-order reference model which can guarantee the expected overshoot and steady-state error. Subsequently, a novel prescribed performance function (PPF) is proposed with a predefined convergence time, and an error transformation method with tangent function is developed. Moreover, by utilizing this PPF structure, a predefined performance attitude tracking error dynamics model is proposed. Based on the predefined-time stable theory, an adaptive predefined-time sliding mode controller with adaptive gain control law is presented and the convergence time can be defined as a prior control parameter, simultaneously. Stability of the proposed controller and the adaptive gain control law are proved by the Lyapunov method. Finally, abundant simulation results verify the predefined performance of the proposed control method.(c) 2021 Elsevier Masson SAS. All rights reserved.
机译：在本文中，研究了高升力发射车辆（HLV）的上升姿态跟踪控制问题，其具有保证的预定义的性能。首先，通过使用二阶参考模型开发了姿态跟踪误差动力学模型，该模型可以保证预期的过冲和稳态误差。随后，提出了一种具有预定义收敛时间的新型规定的性能函数（PPF），并且开发了具有切线函数的误差变换方法。此外，通过利用该PPF结构，提出了一种预定义的性能姿态跟踪误差动力学模型。基于预定义 - 时间稳定理论，提出了一种具有自适应增益控制定律的自适应预定义 - 时间滑模控制器，并将收敛时间同时定义为先前的控制参数。 Lyapunov方法证明了所提出的控制器和自适应增益控制法的稳定性。最后，丰富的仿真结果验证了所提出的控制方法的预定义性能。（c）2021 Elsevier Masson SAS。版权所有。

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