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| 1 | Variational method based robust adaptive control for a guided spinning rocket显示文摘In this paper,a robust adaptive controller is designed for a guided spinning rocket,whose dynamics presents the characteristics of pitch-yaw cross coupling,fast time-varying aerodynamics parameters and wide flight envelop.First,a coupled nonlinear six-degree-of-freedom equation of motion for a guided spinning rocket is developed,and the lateral acceleration motion is modeled as a control plant with time-varying matched uncertainties and unmodeled dynamics.Then,a robust adaptive control method is proposed by combining Bregman divergence and variational method to achieve fast adaption and maintain bounded tracking.The stability of the resulting closed-loop system is proved,and the ultimate bound and convergence rate are also analyzed.Finally,numerical simulations are performed for a single operating point and the whole flight trajectory to show the robustness and adaptability of the proposed method with respect to timevarying uncertainties and unmodeled dynamics. | Zhongjiao Shi Liangyu Zhao Zhijie Liu | 2021 | Chinese Journal of Aeronautics2021，34，3： | 6 |
| 2 | 飞行器抗饱和鲁棒自适应非线性模型预测控制显示文摘针对巡航飞行器同时存在较大外部干扰和模型参数不确定性时自适应预测控制性能下降的问题,设计了带有模糊干扰观测器(fuzzy disturbance observer,FDO)补偿的鲁棒自适应非线性模型预测控制(robust adaptive nonlinear model predictive control,RANMPC)方法(简记为FDO-RANMPC方法)。首先,利用具有未知参数限制条件的递推最小二乘方法在线辨识模型参数;其次,利用模糊干扰观测器输出值抵消幅值较大的复合干扰,再利用Tube鲁棒预测控制策略设计了飞行器底层姿态系统具有稳定保障的FDO-RANMPC控制器;最后,在考虑复合不确定性情况下对指令姿态角跟踪的仿真中验证了控制器的有效性及其渐进稳定性。 | 王超 张胜修 宋仔标 杨建业 吴晓露 | 2018 | 系统工程与电子技术2018，40，2： | 5 |
| 3 | 基于快速终端滑模的机器人轨迹跟踪避障方法显示文摘针对非完整轮式机器人有限时间精准轨迹跟踪避障问题,设计了一种基于全局快速终端滑模方法,兼具无抖振、收敛时间可调等优点的轨迹跟踪控制器。首先,在载体坐标系下建立轮式机器人运动学模型;其次,构造包含终端吸引子和指数收敛项的全局快速终端滑模轨迹跟踪控制器,通过Lyapunov稳定性理论证明了所设计的控制器能确保轨迹与航向角跟踪误差均能在有限时间内收敛于较小的零域范围内;最后,引入人工势场避障方法,实现了机器人严格跟踪参考轨迹的同时绕开障碍物。实验结果表明,该方法能实现在避障的同时对于给定参考轨迹的有限时间稳定跟踪控制。 | 曹志斌 杨卫 邵星灵 刘宁 | 2020 | Journal of Measurement Science and Instrumentation2020，11，1： | 4 |
| 4 | Adaptive fuzzy terminal sliding mode control for the free-floating space manipulator with free-swinging joint failure显示文摘Space manipulator with free-swinging joint failure simultaneously contains kinematic and dynamic coupling relationships,so it belongs to a new underactuated system.To allow the manipulator to carry on tasks,an effective robust underactuated control method for the space manipulator with free-swinging joint failure is studied in this paper.Considering the effect of model uncertainty and joint torque disturbance,a robust underactuated control system based on the Terminal Sliding Mode Controller(TSMC)is designed,but two drawbacks are discussed:(A)Robustness depraves with eliminating chattering.(B)Control parameters are difficult to be determined under unknown uncertainty and disturbance.To improve the TSMC,the adaptive fuzzy controller is introduced to estimate the real effect of unknown uncertainty and disturbance according to deviations of sliding mode and its reaching law.The estimated result is directly compensated into active joints torque.In simulation,the space manipulator with free-swinging joint executes tasks based on the TSMC and the Adaptive Fuzzy Terminal Sliding Mode Controller(AFTSMC)respectively.Same tasks can be finished with smaller joints torque and stronger robustness based on the AFTSMC.Therefore,AFTSMC can serve as an effective robust control method for the space manipulator with free-swinging joint failure under unknown model uncertainty and torque disturbance. | Qingxuan JIA Bonan YUAN Gang CHEN Yingzhuo FU | 2021 | Chinese Journal of Aeronautics2021，34，9： | 2 |
| 5 | 采用奇异摄动裕度的三回路自动驾驶仪设计显示文摘针对传统三回路自动驾驶仪在工程应用中对开环穿越频率约束不足的问题,设计了一种使用奇异摄动裕度的三回路自动驾驶仪方法。该方法将奇异摄动裕度信息引入三回路自动驾驶仪中,对自动驾驶仪进行开环穿越频率极点设计和预测校正,使三回路自动驾驶仪能够有效地对开环穿越频率进行约束,不再依赖于控制系统的闭环自振频率,同时计算得到的奇异摄动值可有效地反映控制系统性能。试验结果分析证明,采用奇异摄动裕度的三回路自动驾驶仪克服了传统设计方法的缺点,对产生的干扰能够有效快速地进行抑制,并能通过奇异摄动值准确地反映控制系统工作效果。 | 张恒浩 | 2018 | 兵工学报2018，39，12： | 2 |
| 6 | Acceleration tracking control for a spinning glide guided projectile with multiple disturbances显示文摘A novel acceleration tracking controller is proposed in this paper, for a Spinning Glide Guided Projectile(SGGP) subject to cross-coupling dynamics, external disturbances, and parametric uncertainties. The cross-coupled dynamics for the SGGP are formulated with mismatched and matched uncertainties, and then divided into acceleration and angular rate subsystems via the hierarchical principle. By exploiting the structural property of the SGGP, model-assisted Extended State Observers(ESOs) are designed to estimate online the lumped disturbances in the acceleration and angular rate dynamics. To achieve a rapid response and a strong robustness, integral sliding mode control laws and sigmoid-function-based tracking differentiators are integrated into the ESO-based Trajectory Linearization Control(TLC) framework. It is proven that the acceleration tracking controller can guarantee the ultimate boundedness of the signals in the closed-loop system and make the tracking errors arbitrarily small. The superiority and effectiveness of the proposed control scheme in its decoupling ability, accurate acceleration tracking performance and antidisturbance capability are validated through comparisons and extensive simulations. | Qi CHEN Xugang WANG Jing YANG Zhongyuan WANG | 2020 | Chinese Journal of Aeronautics2020，33，12： | 0 |
| 7 | 大跨域条件下的自适应滚转稳定容错控制方法显示文摘制导弹药在执行大跨域飞行任务时,其滚转扰动系数随速度、高度和攻角高频大幅值非线性变化,对制导弹药滚转通道稳定性造成了恶劣的影响。此外,时间滞后与控制失效等执行机构动力学特性进一步增加了滚转通道稳定性的控制难度。针对上述问题,设计了一种强鲁棒性的自适应滚转稳定容错控制方法。首先,在考虑执行机构失效动力学特性条件下建立了制导弹药滚转通道的数学模型,将系统不确定性和扰动项视为外部扰动,设计一种基于自适应滑模控制理论的强鲁棒滚转稳定控制方法,以补偿非线性变化项及执行机构失效。在此基础上,进一步考虑了执行机构动力学滞后特性,利用反步法设计了一种考虑执行机构动力学的控制方法,以补偿执行机构动力学滞后特性,提高弹体的响应速度。仿真结果表明所设计控制方法对气动扰动有较强鲁棒性以及在故障处理方面的优势。 | 王雨辰 林德福 王伟 纪毅 | 2021 | 航空学报2021，42，3： | 0 |
| 8 | Robust gain-scheduled missile autopilot design based on multifrequency extended state observers显示文摘This paper describes the design and implementation of a three-axis acceleration control autopilot for an asymmetric tail-controlled,skid-to-turn tactical missile.In an earlier flight test,degraded autopilot performance was attributed to multiple disturbances and uncertainties and the presence of hidden coupling terms,giving rise to a miss distance of greater than 20 m.To address these issues,the missile dynamics are decomposed into the angular rate dynamics as fast and the acceleration dynamics as slow subsystem using the singular perturbation theory to analyze a multi-time-scale property.Multifrequency extended state observers are then incorporated into the gain scheduling technique to attenuate disturbances,thus enhancing the control performance significantly.In the proposed engineering/practical design framework for missile autopilot,simple,conventional,and explicit tuning rules are provided.And the proposed control scheme can achieve input-to-state stability across the entire flight envelope under unknown but bounded disturbances.The advantages of the method over existing benchmark approaches are shown through nonlinear numerical simulations.This is supported by evidence from a new flight test result with a miss distance of only 2 m. | Zonghua SUN Liaoni WU Yancheng YOU | 2023 | Chinese Journal of Aeronautics2023，36，12： | 0 |
| 9 | Leap trajectory tracking control based on sliding mode theory for hypersonic gliding vehicle显示文摘The aim of this study was to develop robust tracking control schemes for the 3D leap trajectory of hypersonic gliding vehicles using sliding mode theory. A predictor-corrector guidance method was applied to the generation of the reference trajectory, and drag acceleration was selected as the profile of reference tracking. A combined super-twisting sliding mode controller(CST-SMC) is proposed to decrease the tracking error and guarantee the tracking performance in the presence of system nonlinearities compared to three other common controllers: the linear sliding mode controller(L-SMC), global fast terminal sliding mode controller(GFT-SMC), and super-twisting sliding mode controller(ST-SMC). By using the developed controller, the system state of a second-order drag acceleration tracking error system can approach the global fast terminal sliding manifold in finite time. By using the Lyapunov approach, sufficient conditions are deduced to ensure that the tracking performance is obtained for a closed-loop system. Furthermore, we show that the controller is robust to initial uncertain parameters and other perturbations, as validated by simulation results with appropriate gains. | Kai AN Zhen-yun GUO Wei HUANG Xiao-ping XU | 2022 | Journal of Zhejiang University-Science A(Applied Physics & Engineering)2022，23，3： | 0 |
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