一种考虑作动器模型的非线性飞行控制律

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• 英文论文题名：A Nonlinear Flight Control Law with Actuator Model Integrated
• 论文作者：章胜 ; 程艳青 ; 钱炜祺 ; 何开锋
• 英文论文作者：Zhang Sheng ; Cheng Yanqing ; Qian Weiqi ; He Kaifeng ; Computational Aerodynamics Institute of China Aerodynamics Research and Development Center
• 年：2016
• 作者机构：中国空气动力研究与发展中心计算空气动力学研究所;
• 论文关键词：过失速机动 ; 飞行控制 ; 非线性控制 ; 时标分离 ; 滑模控制
• 英文论文关键词：post-stall maneuver ; flight control ; non-linear control ; time-scale ; sliding model control
• 会议召开时间：2016-10-31
• 会议录名称：探索 创新 交流（第7集）——第七届中国航空学会青年科技论坛文集（上册）
• 英文会议录名称：Discovery,Innovation and Communication——Proceedings of 7th CSAA Science and Technology Youth Forum
• 语种：中文
• 分类号：V249.1
• 学会代码：ZGHU
• 会议名称：探索 创新 交流（第7集）——第七届中国航空学会青年科技论坛
• 会议地点：中国广东中山
• 主办单位：中国航空学会
• 学会名称：中国航空学会
• 页数：10
• 文件大小：1327k
• 原文格式：O
• 会议级别：全国

摘要

为提高飞机过失速机动品质,减小作动器动态响应对控制的不利影响,提出了一种考虑作动器模型的非线性控制律。基于时标分离原理将对象分为慢回路与快回路,其中慢回路控制器与非线性动态逆控制器类似,但快回路包含作动器模型,设计的滑模控制器在满足作动器性能约束下,充分利用舵面偏转速率能力削减建模误差的影响。由于控制器设计中综合了作动器动力学模型,本文控制律具有控制效果受作动器带宽影响小的良好特性。仿真结果表明,文章给出的控制律比非线性动态逆控制律具有更好的性能,可以有效消除由作动器动态响应引起的控制效果变差的问题。
To attenuate the impairment on the flying qualities originating from the dynamic response of the actuator in the poststall maneuver,a new nonlinear flight controller with the actuator model considered during the design procedure is developed.The plant is separate into the slow loop and fast loop using the time-scale principle.The dynamic inversion technique is employed to obtain the slow-loop controller.In the fast-loop controller design,the actuator model is included and the sliding model controller is derived.Subject to the performance limitation of the actuator,the control surface deflection rate is fully used to counteract the modeling error.The baseline control in the form of deflection rate makes the control effect independent of the bandwidth of the actuator.Simulation results prove the better performance of the controller to the dynamic inversion controller,by attenuating the lag effect on the control from the dynamic response of the actuator.

引文

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