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Analytical geometry-based terminal attack area calculation method for intercepting hypersonic cruise target

Analytical geometry-based terminal attack area calculation m...

引用

IEEE Chinese Guidance, Navigation and control Conference (CGNCC)

作者： Dong Guo Zixuan Liang Qingdong Li Zhang Ren Science and Technology on Aircraft Control Laboratory Beihang University China School of Astronautics Beihang University Beijing China

ISBN: (数字)9781538611715

ISBN: (纸本)9781538611722

This paper presents a terminal attack area (TAA) calculating method based on analytical geometry for intercepting hypersonic cruise aircraft. Firstly, the missile-target planer relative motion model is established, and the intercepting strategy based on analytic geometry is illustrated. Secondly, the intercept geometry models under non-maneuvering and maneuvering target with minimum or maximum initial lead angles are established. Then, based on the intercept geometry models, the analytic solution formulas for calculating the initial feasible attack area are given. Finally, simulation results indicate that the proposed calculation method based on analytical geometry is more accurate and effective than the traditional numerical calculation method.

关键词： Lead Geometry Missiles Atmospheric modeling Analytical models Numerical models aircraft

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L1 adaptive control law design for aircraft considering actuator influence

L1 adaptive control law design for Aircraft considering actu...

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IEEE Chinese Guidance, Navigation and control Conference (CGNCC)

作者： Xiaoxiong Liu Hui Zhao Qingyuan Ma Jian Shen School of Automation Northwestern Polytechnical University Xi’an China Shenyang Aircraft DesignResearch Institute Shenyang China Science and Technology on Aircraft Control Laboratory CFACRI

ISBN: (数字)9781538611715

ISBN: (纸本)9781538611722

Considering the impact of the actuator on the aircraft flight performance, this paper proposes a design method for longitudinal damping control law of aircraft based on Ll adaptive control. Firstly, the aircraft adaptive control model is built according to modeling error and external disturbance of flight control system. And then the actuator model was augmented to the system state vector for accurate pitch rate feedback control. Finally, the Ll adaptive law and observer are designed based on the system structure. The Simulation results show that the Ll adaptive control can perform the longitudinal damping control of the aircraft well, and can still effectively control when the actuator failure.

关键词： aircraft Adaptive control Adaptation models Atmospheric modeling Aerospace control Observers Mathematical model

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Terminal Angle Constrained Integrated Guidance and control for Missile Pitch Channel in the Presence of Input Saturation 29

Terminal Angle Constrained Integrated Guidance and Control f...

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第29届中国控制与决策会议

作者： Guangbin Liu Weihong Wang Sen Wang School of Automation Science and Electrical Engineering Beihang University Science and Technology on Aircraft Control Laboratory Beihang University

ISBN: (纸本)9781509046584

In this paper,in order to attack a fixed target and solve actuator saturation,an integrated guidance and control（IGC） scheme based on LESO and dynamic surface control algorithm with constrained terminal impact angle for missile pitch channel is ***,based on Coriolis theorem,an IGC model for pitch channel is established which does not assume that the initial velocity of the missile coincides with the line-of-sight（LOS） ***,an auxiliary system including a Nussbaum function is introduced to settle actuator *** dynamic surface control algorithm with LESO which is used to estimate the disturbances of the system is designed to track the states of the ***’s more,the stability of the closed-loop system is proved theoretically according to Lyapunov *** simulation results show that the missile can hit the target in desired impact angle stably without input saturation,which reflects validity of the control scheme.

关键词： IGC Fixed Target Input Saturation Terminal Angle Constraint Dynamic Surface control Pitch Channel

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An Image Denoising Method Based on Nonsubsampled Contourlet Transform with SQP Optimization 36

An Image Denoising Method Based on Nonsubsampled Contourlet ...

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第36届中国控制会议

作者： Chen Yang Yaozhong Yu Qingdong Li Xiwang Dong Zhang Ren School of Automation Scicence and Electrical Engineering Science and Technology on Aircraft Control LaboratoryBeihang University

ISBN: (纸本)9781538629185

In this paper,we propose an image demising method based on nonsubsampled contourlet transform(NSCT) with successive quadratic programming(SQP) *** method can obtain the optimal threshold for each subband without the priori information of the noise variance using SQP optimization and generalized cross validation(GCV) *** the threshold is determined,a nonlinear threshold function is applied to overcome the inadequate of soft threshold and hard threshold *** experimental results show that the proposed method has a better performance than other contourlet-based image demising methods and outperforms on both visual quality and peak signal-to-noise ratio(PSNR).

关键词： Image denoising nonsubsampled contourlet transform successive quadratic programming nonlinear threshold function generalized cross validation

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Adaptive Multivariable Finite-Time Reentry Attitude control for RLV 36

Adaptive Multivariable Finite-Time Reentry Attitude Control ...

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第36届中国控制会议

作者： Bailing Tian Yuxin Ma Yunpeng Zhang Qun Zong School of Electrical and Information Engineering Tianjin University Science and Technology on Aircraft Control Laboratory FACRI

ISBN: (纸本)9781538629185

The finite-time tracking control for reusable launch vehicle with matched disturbance is investigated. An adaptivemultivariable controller is proposed where the bounds of the perturbations are not known. A proof of the finite-time convergence of the closed-loop system is derived using the Lyapunov technique. The feature of the proposed control scheme is that it does not require any information on the bounds of the disturbance and its gradient except for their existence. Finally, some simulation tests are provided to demonstrate the effectiveness of the proposed control scheme.

关键词： Adaptive multivariable controller finite-time convergence reusable launch vehicle（RLV）

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Research on Robot Path Planning Based on Fuzzy Neural Network and Particle Swarm Optimization 29

Research on Robot Path Planning Based on Fuzzy Neural Networ...

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第29届中国控制与决策会议

作者： Ying Guo Weihong Wang Sentang Wu School of Automation Science and Electrical Engineering Beihang University Science and Technology on Aircraft Control Laboratory Beihang University

ISBN: (纸本)9781509046584

In a certain evaluation standard,robot path planning is to find a collision-free path from the initial state to the target state in an environment with obstacles,which is one of the key research directions of intelligent mobile *** mathematical model of the surrounding environment is established by using the grid *** obstacle avoidance strategy of the fuzzy neural network is *** function of the obstacle avoidance is realized by searching the next feasible node by the fuzzy neural *** at the parameter optimization problem of fuzzy neural network,the improved particle swarm optimization algorithm is used to optimize the parameters of fuzzy neural network,which avoids the instability of the system caused by improper parameter *** results verify the effectiveness of the *** simulation results show that the path planning of mobile robot based on fuzzy neural network and particle swarm optimization achieves performance index of the minimum sum of the obstacle cost and the route cost.

关键词： Robot Path Planning Particle Swarm Optimization Fuzzy Neural Network

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Research on Adaptive Backstepping control Method for a Hex-rotor Unmanned Aerial Vehicle 29

Research on Adaptive Backstepping Control Method for a Hex-r...

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第29届中国控制与决策会议

作者： Dafu Sheng Weihong Wang Miao Gu School of Automation Science and Electrical Engineering Beihang University Science and Technology on Aircraft Control Laboratory Beihang University

ISBN: (纸本)9781509046584

This paper concentrates on attitude control and position control of the hex-rotor Unmanned Aerial Vehicle(UAV) to achieve fixed-point ***,based on the Newton-Euler equations,the equations of motion are established in the inertial coordinate *** according to the characteristics of the hex-rotor UAV model,adaptive backstepping mode controllers are designed to realize the attitude and position *** Lyapimov theory,the stability of system is ***,simulation results prove that the control system has strong robustness to both the disturbance and the parametric variation.

关键词： the Hex-rotor UAV Model Adaptive Backstepping control Robustness

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Internal Model control/Backstepping Sliding Model control for Quadrotor Trajectory Tracking 2

Internal Model Control/Backstepping Sliding Model Control fo...

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2017 IEEE 2nd Information technology, Networking, Electronic and Automation control Conference (ITNEC 2017)

作者： ZeFang He Long Zhao School of automation science and electrical engineering Beihang University Science and Technology on Aircraft Control Laboratory Beihang University

ISBN: (纸本)9781509064151;9781509064144

The position loop(outer loop) and the attitude loop(inner loop) of a quadrotor are respectively a second-order linear system and a nonlinear system, and the essence of backstepping control is a proportional-derivative(PD) control. When the quadrotor is affected by unmodeled dynamics, parametric uncertainty and aerodynamic disturbance, we design a kind of inner and outer loops hierarchy structure controller to steadily track the quadrotor trajectories, this hierarchy structure controller is that internal model control/backstepping sliding mode controller. Specifically, the backstepping sliding mode controller with strong robustness is used in the inner loop, and two degrees of freedom internal model controller(IMC) only with a feedforward controller adjustment parameter and a feedback controller adjustment parameter is adopted in the outer loop. A stability analysis demonstrates that the close-loop system with this hierarchy structure controller is stable. The effectiveness of the control strategy is tested by tracking a conical spiral and a flight path existing in the literature. Simulation results verify that the quadrotor can steadily track the given fastvarying trajectories and has strong robustness to parameter uncertainties and constant disturbances.

关键词： Trajectory tracking Quadrotor helicopter Shattering free Backstepping sliding mode controller IMC

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UAV autonomous navigation system for GNSS invalidation 36

UAV autonomous navigation system for GNSS invalidation

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第36届中国控制会议

作者： Jingyun Duo Long Zhao School of automation science and electrical engineering Beihang University Science and Technology on Aircraft Control Laboratory Beihang University

ISBN: (纸本)9781538629185

The Global Navigation Satellite System（GNSS） and Strapdown Inertial Navigation System（SINS） integrated navigation system has been widely used on Unmanned Aerial Vehicles（UAVs） ***,the system cannot operates properly when GNSS is *** this paper we propose a systematic framework of visual aided inertial autonomous navigation system to solve this *** proposed system fuses the information of three sub navigation systems such as inertial navigation system,satellite navigation system and visual navigation system *** system gets video information from a monocular camera mounted on a *** the consecutive image frames are matched by detection and matching of oriented FAST and rotated BRIEF（ORB）.An algorithm of treble mismatching point pairs elimination is developed to eliminate outliers,and an optimizing method based on the evaluation of measurements using motion models is developed to reduce *** Kalman filter and multi-rate Kalman filter are both applied to effectuate the positioning of visual aided inertial navigation *** experiments were done based on an own-built multi-rotor *** obtained results show that the proposed system can operate normally and provide accurate navigation information when GNSS is shortly invalid.

关键词： UAV visual odometry integrated navigation Kalman filter

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Time-varying group formation tracking for second-order multi-agent systems with switching directed topologies

Time-varying group formation tracking for second-order multi...

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IEEE Chinese Guidance, Navigation and control Conference (CGNCC)

作者： Yangfan Li Xiwang Dong Qingdong Li Zhang Ren School of Automation Science and Electrical Engineering Science and Technology on Aircraft Control Laboratory Beihang University Beijing P.R. China

ISBN: (数字)9781538611715

ISBN: (纸本)9781538611722

Time-varying group formation tracking problems for second-order multi-agent systems with switching directed topologies are studied, where the followers are divided into subgroups to form pre-defined time-varying sub-formations while tracking the leader of the subgroups that they belong to. Firstly, a time-varying group formation tracking protocol is constructed using local relative state information of each agent and its neighbors. Then an algorithm to design the protocol is proposed. Based on the piecewise Lyapunov function theory, the stability of the proposed algorithm is proven and feasibility constraints as well as the threshold for the dwell time are also presented. Finally, a numerical simulation is provided to demonstrate the effectiveness of the theoretical results.

关键词： Topology Multi-agent systems Switches Time-varying systems Protocols Trajectory

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