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| 1 | Surface-to-air Missile Autopilot Design Using LQG/LTR Gain Scheduling Method显示文摘有环转移恢复(LQG/LTR ) 的线性二次的 Gaussian 获得安排技术被利用设计获得安排为地对空的导弹的自动驾驶仪。以便消除传统的尝试设计进程介绍进系统的人工的无常,基于杆赋值设计目标循环的一个方法被建议,它提供一个明确的算法构造微分 Riccati 方程( MDRE )由性能说明基于期望的杆决定了的矩阵。同时,由介绍综合者扩充工厂动力学, LQG/LTR 的快模式增加安排,这被证明控制器能有效地被制止获得安排,它为 LQG/LTR 的设计申请减轻一个障碍技术。建议方法在为一枚地对空的导弹安排自动驾驶仪的 LQG/LTR 获得的设计被使用。设计和模拟结果显示控制器的快模式显然被消除,并且当飞行马赫数字和高度变化时,自动驾驶仪的动态特征是稳定的。 | YU Jianqiao LUO Guanchen MEI Yuesong | 2011 | Chinese Journal of Aeronautics2011，24，3： | 7 |
| 2 | Observer-based adaptive sliding mode backstepping output-feedback DSC for spin-stabilized canard-controlled projectiles显示文摘This article presents a complete nonlinear controller design for a class of spin-stabilized canard-controlled projectiles.Uniformly ultimate boundedness and tracking are achieved,exploiting a heavily coupled,bounded uncertain and highly nonlinear model of longitudinal and lateral dynamics.In order to estimate unmeasurable states,an observer is proposed for an augmented multiple-input-multiple-output(MIMO) nonlinear system with an adaptive sliding mode term against the disturbances.Under the frame of a backstepping design,an adaptive sliding mode output-feedback dynamic surface control(DSC) approach is derived recursively by virtue of the estimated states.The DSC technique is adopted to overcome the problem of ‘‘explosion of complexity' and relieve the stress of the guidance loop.It is proven that all signals of the MIMO closed-loop system,including the observer and controller,are uniformly ultimately bounded,and the tracking errors converge to an arbitrarily small neighborhood of the origin.Simulation results for the observer and controller are provided to illustrate the feasibility and effectiveness of the proposed approach. | Yuanchuan SHEN Jianqiao YU Guanchen LUO Xiaolin AI Zhenyue JIA Fangzheng CHEN | 2017 | Chinese Journal of Aeronautics2017，30，3： | 4 |
| 3 | Missile robust gain scheduling autopilot design using full block multipliers显示文摘Reduction of conservatism is one of the key and difficult problems in missile robust gain scheduling autopilot design based on multipliers.This article presents a scheme of adopting linear parameter-varying(LPV) control approach with full block multipliers to design a missile robust gain scheduling autopilot in order to eliminate conservatism.A model matching design structure with a high demand on matching precision is constructed based on the missile linear fractional transformation(LFT) model.By applying full block S-procedure and elimination lemma,a convex feasibility problem with an infinite number of constraints is formulated to satisfy robust quadratic performance specifications.Then a grid method is adopted to transform the infinite-dimensional convex feasibility problem into a solvable finite-dimensional convex feasibility problem,based on which a gain scheduling controller with linear fractional dependence on the flight Mach number and altitude is derived.Static and dynamic simulation results show the effectiveness and feasibility of the proposed scheme. | Jianqiao Yu Guanchen Luo Wentao Yin | 2010 | Journal of Systems Engineering and Electronics2010，21，5： | 3 |
| 4 | UAV pathplanning using artificial potential field method updated byoptimal control theory 显示文摘 | Chen Yongbo Luo Guanchen Mei Yuesong | 2014 | International Journal of SystemsScience2014，31，9： | 1 |
| 5 | Missile autopilot design based on robust LPV control显示文摘This paper proposes an effective algorithm to work out the linear parameter-varying(LPV) framework autopilot for the air defense missile so as to simultaneously guarantee the closed-loop system properties globally and locally, which evidently reduces the number of unknown variables and hence increases the computational efficiency. The notion of 'robust quadratic stability' is inducted to meet the global properties, including the robust stability and robust performance, while the regional pole placement scheme together with the adoption of a model matching structure is involved to satisfy the dynamic performance, including limiting the 'fast poles'. In order to reduce the conservatism, the full block multiplier is employed to depict the properties, with all specifications generalized in integral quadratic constraint frame and finally transformed into linear matrix inequalities for tractable solutions through convex optimization. Simulation results validate the performance of the designed robust LPV autopilot and the proposed framework control method integrating with the full block multiplier approach and the regional pole placement scheme, and demonstrate the efficiency of the algorithm. An efficient algorithm for the air defense missile is proposed to satisfy the required global stability and local dynamical properties by a varying controller according to the flight conditions, and shows sufficient promise in the computational efficiency and the real-time performance of the missile-borne computer system. | Yuanchuan Shen Jianqiao Yu Guanchen Luo Yuesong Mei | 2017 | Journal of Systems Engineering and Electronics2017，28，3： | 0 |
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