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A quantum inspired genetic algorithm for multimodal optimization of wind disturbance alleviation flight control system

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Chinese Journal of Aeronautics 2019年第11期32卷 2480-2488页

作者： Qi BIAN Brett NENER Xinmin WANG School of Automobile Chang’an UniversityXi’an 710064China Department of Electrical Electronicsand Computer EngineeringThe University of Western AustraliaCrawley 6009WAAustralia School of Automation Northwestern Polytechnical UniversityXi'an 710129China

This paper develops a Quantum-inspired Genetic Algorithm(QGA) to find the sets of optimal parameters for the wind disturbance alleviation flight control system(FCS). To search the problem domain more evenly and uniformly, the lattice rule based stratification method is used to create new chromosomes. The chromosomes are coded and updated according to quantuminspired strategies. A niching method is used to ensure every chromosome can converge to its corresponding local minimum in the optimization process. A parallel archive system is adopted to monitor the chromosomes on-line and save all potential feasible solutions in the optimization process. An adaptive search strategy is used to gradually adjust the search domain of each niche to finally approach the local minima. The solutions found by the QGA are compared with some other Multimodal Optimization(MO) algorithms and are tested on the FCS of the Boeing 747 to demonstrate the effectiveness of the proposed algorithm.

关键词： flight control system Genetic algorithm Multimodal optimization Quantum inspired algorithm Wind disturbance alleviation

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Design of Missile flight control system Based on Variable Structure control Theory 36

Design of Missile Flight Control System Based on Variable St...

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第36届中国控制会议

作者： Jiang Lou Zhihao Cai Jiang Zhao Kun Wu Yingxun Wang School of Automation Science and Electrical Engineering Beihang University

ISBN: (纸本)9781538629185

flight control system plays an important role in the process of missile *** quality of flight control system will affect the missile’s performance *** this article,we design a flight control system using variable structure control ***,we establish a mathematical model of the missile and the basic content of variable structure control theory is *** chapter are mainly aiming at designing the control system of the missile’s normal ***,the linearized missile’s normal overload is designed by using the mathematical model in chapter *** the variable structure controller is *** addition,we use the variable structure controller to optimize the linear normal load control *** numerical simulation of two different control methods are *** the result illustrate that the robustness of the control system based on variable structure theory are better.

关键词： flight control system linearization control variable structure control

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Actuator Fault Diagnosis for flight control system Based on Sliding Mode Observer

Actuator Fault Diagnosis for Flight Control System Based on ...

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第30届中国控制与决策会议

作者： Lu Quan Bin Jiang Pu Yang College of Automation Engineering Nanjing University of Aeronautics and Astronautics

In this paper, a sliding mode observer based fault diagnosis method was proposed for a class of linear systems with the disturbance and model uncertainty to detect the actuator faults. The difficulty on the sliding mode observer method can be directly solved by using linear matrix inequalities（LMIS）. The stability of the designed sliding mode observer can be guaranteed by Lyapunov stability theory. The proposed actuator fault diagnosis method is tested in a 3-DOF aircraft simulation platform to illustrate the performance of the proposed observer and the effectiveness of the fault diagnosis algorithm.

关键词： Sliding mode observer Fault diagnosis flight control system

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Motion blurred image restoration based on flight control system

Motion blurred image restoration based on flight control sys...

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第37届中国控制会议

作者： Ran Zhao Dongliang Liu Feng Qu Xu Zhang Academy of Automation Hangzhou Dianzi University Wolong Electric CO. LTD

In recent years, the applications of Aerial UAV are more and more extensive. The aerial system is subject to the impact of the relative movement, posture changes and the atmosphere, which results in low clarity of the captured image. Based on the image blur phenomenon caused by UAV flight, a function is introduced as its coefficient in Lucy-Richardson（LR） image restoration algorithm, which could effectively protect edge details of the image. The results of image quality evaluation show that the improved LR algorithm can effectively suppress the noise in the image and improve the clarity of the image.

关键词： flight control system image restoration Motion blur LR algorithm Evaluation of Image quality

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Hardware Design of flight control system and flight Experiments of Small-Scale Unmanned Aerial Vehicle

Hardware Design of Flight Control System and Flight Experime...

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第32届中国控制与决策会议

作者： Xinfan Yin Kaiming Xu Huayou Liang Guichuan Zhang Xianmin Peng Qiuyun Zhang Low Speed Aerodynamics Institute of China Aerodynamics Research and Development Center School of Electronics Engineering and Computer Science Peking University Southwest University of Science and Technology

In view of the strict requirements of small-scale unmanned aerial vehicle on the performance,volume and weight of flight control system,this paper presents a hardware design of flight control system based on STM32 F103 RCT6 *** accordance with the system function and interface characteristics,the flight control system is divided into power module,main control module,sensor module and interface drive module,which meet the technical requirements of high integration,low coupling and expansibility of the flight control *** to the characteristics of different types of sensor units integrated in the system,we design the interface circuit of inertial sensor,barometer and geomagnetic sensor based on I2 C bus and GPS interface circuit based on *** flight experiments are carried out on the small-scale quadcopter *** results show that the flight control system designed in this paper has good practicability and high reliability,and meets the requirements of the small-scale unmanned aerial vehicle for the function and performance of the flight control system.

关键词： Unmanned aerial vehicle flight control system hardware design interface circuit flight experiment

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Design of multi-UAVs flight control system and trajectory planning

Design of multi-UAVs flight control system and trajectory pl...

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第37届中国控制会议

作者： Juntong Qi Tong Ding Xiang Lu School of Electrical and Information Engineering Tianjin University

With the increase of Unmanned Aerial Vehicle（UAV） mission’s complexity,single UAV is limited to energy and load constraints,and cannot complete mission ***,human is prone to fatigue and slow reaction time in UAV’s flight ***,it is very important to design a control system to accomplish the task of multi-UAVs formation flying *** order to complete formation flight,trajectory planning is also an important *** this paper,we completed the design of four kinds of flight formation,designed and implemented a new multi-UAVs formation flight control *** consists of three subsystems:UAV control system,motion control system and ground station control *** formation flight experiment was carried out,and we analyzed the effect of trajectory planning and flight control system from three aspects:track following effect,velocity and the distance of *** average deviation of the whole trajectory is0.021 meter,and the max deviation is 0.156 meter when the velocity is 1.6238 meter/s,which has no effect on the formation *** formation flight control system designed in this paper can accomplish the task of formation flight stably,which is helpful to make a deeper study of the multi-UAVs formation flight.

关键词： Formation trajectory planning flight control system Trajectory tracking

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Development of a Lateral-directional Envelop Protection flight control system

Development of a Lateral-directional Envelop Protection Flig...

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2012年计算机应用与系统建模国际会议

作者： Liu Fan Wang Lixin School of Aeronautic Science and Engineering Beihang University

For the factor of aircraft flying safety, some critical flight parameters must be limited within the envelop borders. However, excellent flight performance requires that the aircraft can flight to some envelop borders easily and fast nearly. The purpose of envelop protection is to solve this dilemma. Based on the basic lateral-directional flight control law, an envelop protection method using control command compensation is developed. Numerical simulation results show that this method can effectively solves the flying safety problem without sacrificing flight performance.

关键词： Aircraft Envelop protection Envelop limit Command compensation flight control system Lateral-directional control Simulation

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Design of Tiltrotor flight control system Using Optical control

Design of Tiltrotor Flight Control System Using Optical Cont...

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第二十六届中国控制会议

作者： Fan Yonghua 1,Yang Jun 2 1.College of Automation,Northwestern Polytechnical University,Xi''an 710072,P.R.China2.College of Astronautics,Northwestern Polytechnical University,Xi''an 710072,P.R.China

Tiltrotor can flight both airplane mode and helicopter mode by changing the propulsion thrust vector via angle of *** tiltrotor has performance of vertical and short take-off and land（V/STOL）,multi-purpose aircraft with ex-cellent high-speed ***,it is very difficult to design the flight control system for transforming the flight mode be-cause both thrust vector and aerodynamic force are *** the model of the tiltrotor is given,and then the method of optical control is present to design the flight control *** power of propeller constant conversion scheme that is supporting the power of the propeller is constant while tiltrotor coverts the flight mode has been *** the flight control system is simulated and the simulation results have been proved that the flight control system is feasible.

关键词： Tiltrotor flight control system Optical control Conversion Scheme

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Design of flight control system for Tiltrotor Conversion Using QFT

Design of Flight Control System for Tiltrotor Conversion Usi...

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第26届中国控制与决策会议

作者： Lu Ke Wang Zhengzhong Cheng Qiyou National Key Laboratory of Rotorcraft Aeromechanics CHRDI

ISBN: (纸本)9781479937097

Quantitative feedback theory（QFT） is a robust control design method. QFT quantitatively mirror the system uncertainty and design performance target to the Nichols chart, so the designed control system could ensure the performance. Due to the parameter uncertainty in tiltrotor conversion process, using QFT method design the flight control system for tiltrotor conversion. Simulation shows that the controller has a good robust performance.

关键词： Quantitative feedback theory Tiltrotor flight control system

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Initial virtual flight test for a dynamically similar aircraft model with control augmentation system

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Chinese Journal of Aeronautics 2017年第2期30卷 602-610页

作者： Guo Linliang Zhu Minghong Nie Bowen Kong Peng Zhong Chengwen School of Aeronautics Northwestern Polytechnical University Low Speed Aerodynamics Institute China Aerodynamics Research and Development Center

To satisfy the validation requirements of flight control law for advanced aircraft,a wind tunnel based virtual flight testing has been implemented in a low speed wind tunnel.A 3-degree-offreedom gimbal,ventrally installed in the model,was used in conjunction with an actively controlled dynamically similar model of aircraft,which was equipped with the inertial measurement unit,attitude and heading reference system,embedded computer and *** model,which could be rotated around its center of gravity freely by the aerodynamic moments,together with the flow field,operator and real time control system made up the closed-loop testing *** model is statically unstable in longitudinal direction,and it can fly stably in wind tunnel with the function of control augmentation of the flight control *** experimental results indicate that the model responds well to the operator＇s *** response of the model in the tests shows reasonable agreement with the simulation *** difference of response of angle of attack is less than 0.5°.The effect of stability augmentation and attitude control law was validated in the test,meanwhile the feasibility of virtual flight test technique treated as preliminary evaluation tool for advanced flight vehicle configuration research was also verified.

关键词： 3-degree-of-freedom gimbal Dynamic test flight dynamics simulation flight control system Real time Wind tunnel

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