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共 1299 条记录，以下是71-80 订阅

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ADAPTIVE ITERATIVE LEARNING TORQUE control OF ELECTRO-HYDRAULIC LOAD SIMULATOR

ADAPTIVE ITERATIVE LEARNING TORQUE CONTROL OF ELECTRO-HYDRAU...

引用

2024 CSAA/IET International Conference on aircraft Utility Systems, AUS 2024

作者： Shu, Sheng Wu, Shuai School of Automation Science and Electrical Engineering Beihang University Beijing China National Key Laboratory of Aircraft Integrated Flight Control Beihang University Beijing China Key Laboratory of Advanced Aircraft Systems Beihang University Ministry of Industry and Information Technology Beijing China Ningbo Institute of Technology Beihang University Ningbo China

The electro-hydraulic load simulator which can simulate the load executed on the aircraft actuator in the process of flight is an important ground test equipment. The uncertainties of the system including the disturbances caused by the motion of actuator make it challenging to achieve high performance. This study develops an adaptive iterative learning controller for the torque control of electro-hydraulic load simulator utilizing the backstepping method. On the basis of adaptive backstepping control, this controller incorporates iterative learning law to learn unknown nonlinear functions. By utilizing the repetitive characteristic of the test equipment, the iterative learning law sacrifices learning time to achieve enhanced control performance. To handle unknown disturbances, filter error, and learning error, a robust term described by dynamic equations is constructed. The calculation of the derivative of the virtual control law is simplified with a first-order command filter. Simulations with three different controllers are obtained to illustrate the learning ability of the proposed controller. © The Institution of Engineering & technology 2024.

关键词： Backstepping

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Construction of the RMST Indicator System for Aeronautical Complex Equipment Based on Correlation Analysis and Fuzzy-rough Set Theory 2

Construction of the RMST Indicator System for Aeronautical C...

引用

2022 2nd International Conference on Mechatronics technology and Aerospace Engineering, ICMTAE 2022

作者： Hu, Gexi Gong, Feng Liu, Hengchang Yao, Fengming Li, Bo School of Aeronautics and Astronautics University of Electronic Science and Technology of China China Aircraft Swarm Intelligent Sensing and Cooperative Control Key Laboratory of Sichuan Province University of Electronic Science and Technology of China China

To solve the problem of the lack of a scientific indicator system in the current RMST research of complex aeronautical equipment, we focused on the construction principle of science and followed the six principles, including objective, complete, workable, independent, significant, and dynamic. We have adopted subjective methods to collect the RMST of indicators in all aspects. Then the redundant indicators with large correlation coefficients were eliminated sequentially using correlation analysis, and the indicators that did not have a significant impact on the evaluation results were eliminated using fuzzy rough set theory. In order to avoid the redundancy of indicators while ensuring the retention of significant indicators, a scientific and concise RMST indicator system was finally constructed, which filled the gap of the current RMST indicator system for aeronautical complex equipment. © Published under licence by IOP Publishing Ltd.

关键词： Rough set theory

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Trajectory Optimization and control Algorithm of Perch Landing for Fixed-Wing aircraft

Trajectory Optimization and Control Algorithm of Perch Landi...

引用

International Conference on Guidance, Navigation and control, ICGNC 2022

作者： Wang, Guanjie Song, Kepu Zhang, Xianglun AVIC Xi’an Flight Automatic Control Research Institute Xi’an710076 China National Key Laboratory of Science and Technology on Aircraft Control Xi’an710076 China AVIC Xi’an Aircraft Industry Group Company Ltd. Xi’an710089 China

ISBN: (纸本)9789811966125

Recent years, many researches have begun to study bird-like perch landing method. The advantage of perch landing for fixed-wing aircraft is that the landing time and space can be saved. However, the control problem of perch landing for fixed-wing aircraft at the high angle of attack is challenging because of the rapid change of the angle of attack and the unsteady airflow field. This paper considers the control problem of nonlinear motion equations with high angle of attack caused by perch landing, plans perch landing trajectory on the nonlinear motion model by the optimal control theory, and designs longitudinal control law based on system identification and lateral control law based on dynamic inverse. The simulation results show that compared with regular landing, the landing time and space can be significantly shortened by perch landing. Besides, the perturbation test results reveal good accuracy and stability of control algorithm. © 2023, The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.

关键词： Equations of motion

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Dynamic stiffness simulation analysis of hydraulic dual-parallel actuation systems using Amesim

Dynamic stiffness simulation analysis of hydraulic dual-para...

引用

2024 CSAA/IET International Conference on aircraft Utility Systems, AUS 2024

作者： Li, Chuandong Wu, Shuai Wei, Renlei Chen, Taiqi Qin, Mingyuan Chu, Bing Yang, Yuliang Luo, Jianing School of Automation Science and Electrical Engineering Beihang University Beijing100191 China National Key Laboratory of Aircraft Integrated Flight Control Beihang University Beijing100191 China AVIC Shenyang Aircraft Design and Research Institute Ministry of Industry and Information Technology Beijing100191 China Key Laboratory of Advanced Aircraft Systems Beihang University Ministry of Industry and Information Technology Beijing100191 China

In the field of flight control systems, actuators play a crucial role, and dynamic stiffness stands as one of the pivotal metrics to gauge their performance, reflecting the actuators' resilience to external disturbances. Hence, investigating dynamic stiffness is paramount for enhancing the overall performance of flight control systems. This study focuses on a hydraulic dual-parallel actuator system, wherein a mathematical model is established to derive the expression for dynamic stiffness. Leveraging the Amesim software, a simulation model of the parallel actuator system is constructed to conduct an in-depth analysis of its dynamic stiffness characteristics. During simulation, sinusoidal loading forces of varying frequencies are applied at the output end of the actuator system, and displacement response data is collected. Subsequently, the Fast Fourier Transform (FFT) is employed to obtain dynamic stiffness, enabling an analysis of its variations. The relationship between the system's natural frequency and dynamic stiffness is explored, along with an investigation into the primary factors influencing dynamic stiffness. Simulation results indicate that enhancing both support and connection stiffness,reducing load mass and enlarging the piston area can enhance the system's dynamic stiffness, thereby meeting the performance requirements of flight control systems. © The Institution of Engineering & technology 2024.

关键词： Fast Fourier transforms

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Fault-Tolerant Integrated Guidance and control Design for Hypersonic Vehicle Based on ADRC 3rd

Fault-Tolerant Integrated Guidance and Control Design for Hy...

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3rd International Conference on Autonomous Unmanned Systems, ICAUS 2023

作者： Yan, Guocheng Wang, Honglun Wu, Tiancai Wu, Xingyu School of Automation Science and Electrical Engineering Beihang University Beijing100191 China Science and Technology on Aircraft Control Laboratory Beihang University Beijing100191 China Shenyuan Honors College Beihang University Beijing100191 China

ISBN: (纸本)9789819711062

To ensure the stability and safety of hypersonic vehicle reentry flights, we have designed a fault-tolerant integrated guidance and control (FTIGC) system using active disturbance rejection control (ADRC) theory. This system takes into account the presence of multiple uncertain factors and potential actuator malfunctions, which could compromise the vehicle’s trajectory. First, to tackle the issue of error caused by the association between individual guidance and control loop designs, a 6 DOF model of hypersonic vehicles and fault model of actuator are established. Then, predictor-corrector guidance law based on quasi-equilibrium glide condition (QEGC) is employed in guidance loop. In fault-tolerant control system, active disturbance rejection controllers are designed in attitude loop and angular loop respectively. Finally, under the condition of without and with actuator faults, the simulations are conducted. The effectiveness of the FTIGC system based on ADRC theory is verified through the simulation result. © Beijing HIWING Scientific and Technological Information Institute 2024.

关键词： Hypersonic vehicles

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Formation Optimization Method of Multiple Hypersonic Vehicles

Formation Optimization Method of Multiple Hypersonic Vehicl...

引用

International Conference on Guidance, Navigation and control, ICGNC 2022

作者： Zhang, Yuqing Yu, Jianglong Dong, Xiwang Li, Qingdong Ren, Zhang Institute of Artificial Intelligence Beihang University Beijing100191 China School of Automation Science and Electrical Engineering Science and Technology on Aircraft Control Laboratory Beihang University Beijing100191 China

ISBN: (纸本)9789811966125

This paper constructed a collaborative combat effectiveness evaluation system with considering the characteristics and limitations of the vehicles. Firstly, multiple hypersonic vehicles formation problem is converted to an optimization problem based on the collaborative combat effectiveness evaluation system. Secondly, the relative distance and angles between vehicle and a certain reference point is selected as the formation parameters, which are chosen as optimization variables in the optimization algorithm. Thirdly, the efficiency function corresponding to each evaluation indicator is given under the constraints of the vehicle and the PSACO (particle swarm ant colony optimization) algorithm is used to solving this optimization problem. In particular, the scenario of detection and the scenario of penetration are designed respectively considering different combat requirements. Finally, it can be verified that multiple hypersonic vehicles can achieve cooperative optimal formation in two combat scenarios through the effectiveness evaluation system and the PSACO algorithm according to simulation examples. © 2023, The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.

关键词： Hypersonic vehicles

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Online Generation of Smooth Gliding Re-entry Trajectory

Online Generation of Smooth Gliding Re-entry Trajectory

引用

International Conference on Guidance, Navigation and control, ICGNC 2022

作者： Hu, Cunyi Wang, Chenyu Wu, Yunjie State Key Laboratory of Virtual Reality Technology and System Beihang University Beijing100191 China School of Automation Science and Electrical Engineering Beihang University Beijing100191 China Science and Technology On Aircraft Control Laboratory Beijing100191 China

ISBN: (纸本)9789811966125

Since the 21st century, the trajectory planning of hypersonic vehicles has become a major focus and difficulty of research due to their ability to strike targets rapidly. In this paper, a mathematical model of the re-entry corridor under the altitude-velocity profile is established, and the initial altitude range is obtained by using the initial descent method. The proposed equilibrium gliding condition is used to suppress the periodic altitude bounce within the remaining range while introducing the angle feedback. It is also studied in comparison with two cases. In the first case, a comparative study is performed with the method without feedback, and the second case is the application of the algorithm introducing altitude feedback in the predictor-corrector guidance algorithm to this trajectory planning. The experimental results show that this method can make the trajectory descend according to the altitude-velocity trajectory curve obtained from the preset equilibrium gliding angle, so as to obtain the three-degree-of-freedom re-entry trajectory and complete the online generation and tracking of the three-degree-of-freedom trajectory. © 2023, The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.

关键词： Trajectories

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A Composite Terminal-Guidance Method Considering No-Fly Zone Avoidance and Impact Angle Constraint 3rd

A Composite Terminal-Guidance Method Considering No-Fly Zone...

引用

3rd International Conference on Autonomous Unmanned Systems, ICAUS 2023

作者： Wu, Xingyu Wang, Honglun Ren, Bin Wu, Tiancai Yan, Guocheng School of Automation Science and Electrical Engineering Beihang University Beijing100191 China Science and Technology On Aircraft Control Laboratory Beihang University Beijing100191 China Shenyuan Honors College Beihang University Beijing100191 China

ISBN: (纸本)9789819711062

To address the problem of no-fly zone avoidance and impact angle constraint in the terminal-guidance phase, a composite terminal-guidance method is proposed. First, to facilitate the design of the algorithm, the dynamic equations of the missile and no-fly zone model are established. Then, to address the problem of impact angle constraint, the arbitrary time convergent impact angle constrained guidance (ATC-IACG) which enables the impact angel to converge to the desired angle at the specific time is introduced. Traditional ATC-IACG is designed in two-dimensional plane, and this paper extends it to the three-dimensional space. Besides, to address the problem of avoiding the no-fly zone, the interfered fluid dynamical system (IFDS) algorithm is introduced and combined with ATC-IACG, proposing a composite terminal-guidance method considering no-fly zone avoidance and impact angle constraint (ATC-IACG-IFDS) and achieving no-fly zone avoidance and advance convergence of the impact angle in the terminal-guidance phase. At last, the simulation results in this paper verify the effectiveness of the proposed composite terminal-guidance method. © Beijing HIWING Scientific and Technological Information Institute 2024.

关键词： Dynamical systems

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Vision-Based Intelligent Grasping System for Moving Object

Vision-Based Intelligent Grasping System for Moving Object

引用

International Conference on Guidance, Navigation and control, ICGNC 2022

作者： Wang, Chenyu Hu, Cunyi Wu, Yunjie State Key Laboratory of Virtual Reality Technology and System Beihang University Beijing100191 China School of Automation Science and Electrical Engineering Beihang University Beijing100191 China Science and Technology on Aircraft Control Laboratory Beijing100191 China

ISBN: (纸本)9789811966125

The grasping of moving objects is a widely studied application direction of manipulator. Because of the continuous change of the object position and shape, it is difficult to detect and track it. In this article, we propose an object detection and tracking algorithm based on the cascade of YOLOv4 and DSST. The algorithm can detect the object automatically and then track it steadily. It turns out that the algorithm realized accurate detection, real-time tracking and exact grasping of moving objects, and solved the problems of target loss in the tracking process. Through this algorithm and stereo vision method, we can further obtain the 3-D position of our target. Using Aubo-i5 manipulator and Intel RealSense D435 RGBD depth camera, we build a vision-based grasping system for moving object with the above algorithm, which achieved good real-time performance in the practical grasping experiments, and completed the accurate grasping of moving objects. © 2023, The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.

关键词： Object detection

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A Novel Automatic Carrier Landing System with ADRC-Based controller and LSTM-Based Compensation Method 3rd

A Novel Automatic Carrier Landing System with ADRC-Based Con...

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3rd International Conference on Autonomous Unmanned Systems, ICAUS 2023

作者： Zhu, Junfan Wang, Honglun Zhang, Menghua Ren, Bin Wu, Tiancai School of Automation Science and Electrical Engineering Beihang University Beijing100191 China The Science and Technology on Aircraft Control Laboratory Beihang University Beijing100191 China Shenyuan Honors College Beihang University Beijing100191 China

ISBN: (纸本)9789819710980

Aiming at the problem of carrier-based aircraft automatic carrier landing, this paper proposes a new automatic carrier landing system (ACLS) design with controller based on active disturbance rejection control (ADRC) and deck motion compensation (DMC) method with long short-term memory (LSTM) prediction. First, the six degrees of freedom nonlinear dynamic model of carrier-based aircraft and the deck motion model of aircraft carrier are established. Second, to improve the anti-disturbance performance of ACLS, the ADRC-based controller is introduced to be the inner loop controller. Third, due to the advantage in predicting long time series data, LSTM recurrent neural network is used to make prediction of deck motion and combined with the controllers of ACLS, the method of DMC is introduced. Finally, the methods proposed in this paper are verified by simulation. The simulation results show that the ADRC-based controller have better anti-disturbance performance in windy environment compared with traditional controller, and combined with DMC method, the whole system can track the motion of desired touchdown point (DTP) with the tracking error is in range of ±0.6 m. © Beijing HIWING Scientific and Technological Information Institute 2024.

关键词： Long short-term memory

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