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5th China aviation science and technology Conference, 2021

作者： Kuan, Lu Aijun, Li Tianbo, Wang Linxiao, Li Jianyuan, Wang Northwestern Polytechnical University Xi’an710129 China AVIC Xi’an Flight Automatic Control Research Institute Xi’an710065 China National Key Laboratory of Science and Technology On Aircraft Control Xi’an710065 China

ISBN: (纸本)9789811674228

It is the first time that domestic civil large aircraft has been developed, which lacks the technical experience of airborne system-level airworthiness qualification, and the research of radiation emission at home and abroad is mainly based on simulation evaluation, while the simulation results are used only as a reference in the airworthiness qualification process and cannot be used as evidence of conformity. And there is little airworthiness test experience on complex system-level. In this paper, taking civil aircraft flight control electronic system as an example, through the demonstration of the airworthiness requirement, the description of the complexity of civil aircraft flight control electronic system, demonstrate the airworthiness qualification test and optimization process, providing experience for the airworthiness qualification of civil aircraft complex system. The results show that the radiation emission of flight control electronic system is greatly affected by the system environment, and it is necessary to consider the test setup layout and show the system compliance to the DO-160G requirements. © 2022, The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.

关键词： Aircraft control

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GPIO Based Iterative Learning control for Manipulators with Time-Varying Disturbances 42

GPIO Based Iterative Learning Control for Manipulators with ...

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42nd Chinese control Conference, CCC 2023

作者： Lu, Huangyuwei Wang, Zuo Sun, Jiankun Xiao, Xi Li, Shihua School of Automation Southeast University Nanjing210096 China Key Laboratory of Measurement and Control of Complex Systems of Engineering Ministry of Education Nanjing210096 China Shenzhen Research Institute Southeast University Shenzhen518063 China School of Artificial Intelligence and Automation Huazhong University of Science and Technology Wuhan430074 China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing211106 China

ISBN: (纸本)9789887581543

To improve the disturbance rejection ability and repetitive tracking accuracy of manipulators, a composite iterative learning control (ILC) scheme via generalized proportional integral observer (GPIO) is proposed. A high-order polynomial is first employed to model the time-varying disturbances that include unmodeled dynamics, parameter uncertainties and load fluctuations. A GPIO is then designed to estimate the disturbances and high-order time derivatives. By introducing estimations into a PD-type ILC at each iteration, a composite control scheme is obtained, such that the undesirable influence of time-varying disturbances can be effectively attenuated in the repetitive tracking process of manipulators. In this paper, the rigorous stability analysis of the closed-loop system is presented to guarantee that the tracking error exponentially converges to zero as the iteration number tends to infinity. The effectiveness of the proposed control scheme is finally verified by simulation results. © 2023 Technical Committee on control Theory, Chinese Association of Automation.

关键词： Disturbance rejection

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Multi-target Emergency Rescue Path Planning in Marine Wind and Wave Environments 3

Multi-target Emergency Rescue Path Planning in Marine Wind a...

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2022 3rd International Conference on Mechanical Engineering and Materials, ICMEM 2022

作者： Sun, Zhi Yu, Yuanyuan Mei, Yiying Xiao, Xunqiao Shi, Zicang Key Laboratory of Civil Aviation Emergency Science and Technology CAAC Nanjing University of Aeronautics and Astronautics Nanjing211106 China Key Laboratory of Aircraft Environment Control and Life Support MIIT Nanjing University of Aeronautics and Astronautics Nanjing210016 China

With the development of marine-related industries, the number of tasks at sea has increased, and accidents there happen more frequently as well. Search and rescue are very challenging because of the extreme wind and wave environment at sea. Therefore, the state has been paying more attention to maritime emergency rescue. One part is emergency rescue path planning, which is crucial for helicopter emergency rescue at sea. In this paper, a series of multi-target rescue path solutions are created in order to solve the challenge of multi-target rescue path planning while taking into account sea wind and waves. The rescued targets' floating trajectory model is first established. Then, a recursive algorithm based on a permutation tree is given in response to the unsteady change of the targets' position at sea. The rescue path is planned with the goal of cutting down on the helicopter's search time. Finally, using the multi-target rescue in China's Taiwan Strait as an example, it is discovered that the overall time needed for the multi-target rescue is decreased by 7.03 minutes, and the efficiency of the rescue is improved by 13.3% in the wind and wave environment at sea. According to the research, the optimal rescue path shortens the time required for multi-target rescue at sea while increasing the effectiveness of helicopter rescue operations. © Published under licence by IOP Publishing Ltd.

关键词： Motion planning

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A Rapid and Integrated Modeling Method of Aircraft Vulnerability Based on CATIA Analysis Simulation Module 5th

A Rapid and Integrated Modeling Method of Aircraft Vulnerabi...

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5th China aviation science and technology Conference, 2021

作者： Pei, Yang Shi, Likuan Ge, Yuxue Li, Mingsuo Bai, Chunyu Zhang, Yu School of Aeronautics Northwestern Polytechnical University Xi’an710072 China Science and Technology on Electro-Optic Control Laboratory Luoyang471009 China Aviation Key Laboratory of Science and Technology on Structures Impact Dynamics Aircraft Strength Research Institute of China Xi’an710065 China

ISBN: (纸本)9789811674228

Aircraft vulnerability modeling is the basis and prerequisite for vulnerability analysis. At present, vulnerability modeling methods include combinatorial geometry, triangular patch, and tetragonal patch. However, these methods have disadvantages such as low modeling accuracy, complex modeling process, and finite element software. Under the problems of the above methods, a vulnerability modeling method is proposed based on the CATIA Analysis Simulation module, in which the secondary development of the aircraft shape and the tetragonal mesh, materials, and attribute of the components data file are completed. In this method, the geometrical modeling and meshing are synchronized and integrated into the CATIA platform which shortens the vulnerability pre-modeling process. Taking the US "Scan Eagle" UAV as an example, the input model file for vulnerability analysis is generated. The effect of this method and the traditional finite element modeling method is compared in C and K kill levels, which verifies the validity and usability of the proposed method. © 2022, The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.

关键词： Aircraft

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Helicopter Rotor Fault Diagnosis based on IPSO and RVM 14

Helicopter Rotor Fault Diagnosis based on IPSO and RVM

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14th IEEE Global Reliability and Prognostics and Health Management Conference, PHM-Hangzhou 2023

作者： Si, Xiaoyi Zheng, Liang Zheng, Guo Wang, Jinglin Zhao, Zhenping Guo, Ziang School of Electronic Information Hangzhou Dianzi University Hangzhou China AVIC United Technology Center for Basic Research on Aircraft System Fault Diagnosis and Health Management Shanghai Institute of Aerospace Control Engineering Shangai China Aviation Key Laboratory of Science and Technology on Fault Diagnosis and Health Management Shanghai Institute of Aerospace Control Engineering Shangai China

ISBN: (纸本)9798350301359

To address the issue of low accuracy in traditional rotor fault diagnosis during the helicopter rotor fault diagnosis process, this paper presents a fault diagnosis method based on the Improved Particle Swarm Optimization (IPSO) algorithm for Relevance Vector Machine (RVM). The fitness function of the IPSO algorithm is defined as the mean squared error between the predicted classification results obtained through cross-validation and the actual classification. The IPSO algorithm is used to search for the optimal width factor of the RVM kernel function and establish the fault diagnosis model. Through simulation experiments and comparisons with Particle Swarm Optimization (PSO) algorithm-based RVM and Improved Particle Swarm Optimization-based Support Vector Machine (SVM), it is demonstrated that this approach, compared to traditional rotor fault diagnosis methods, effectively improves the accuracy of fault recognition. © 2023 IEEE.

关键词： Fault Diagnosis Helicopter Rotor Improved Particle Swarm Optimization Relevance Vector Machine

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High-order compact gas-kinetic schemes for three-dimensional flow simulations on tetrahedral mesh

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Advances in Aerodynamics 2023年第1期5卷 1-28页

作者： Fengxiang Zhao Xing Ji Wei Shyy Kun Xu Department of Mechanical and Aerospace Engineering Hong Kong University of Science and TechnologyClear Water BayKowloonHong KongChina Department of Mathematics Hong Kong University of Science and TechnologyClear Water BayKowloonHong KongChina Shaanxi Provincial Key Laboratory of Environment and Control for Flight Vehicles Xi’an Jiaotong UniversityXi’anChina Center for Ocean Research in Hong Kong and Macao(CORE) Hong Kong University of Science and TechnologyClear Water BayKowloonHong KongChina Shenzhen Research Institute Hong Kong University of Science and TechnologyShenzhenChina

A general framework for the development of high-order compact schemes has been proposed *** core steps of the schemes are composed of the following.1).Based on a kinetic model equation,from a generalized initial distribution of flow variables construct a time-accurate evolution solution of gas distribution function at a cell interface and obtain the corresponding flux function;2).Introduce the WENO-type weighting functions into the high-order time-derivative of the cell interface flux function in the multistage multi-derivative(MSMD)time stepping scheme to cope with the possible impingement of a shock wave on a cell interface within a time step,and update the cell-averaged conservative flow variables inside each control volume;3).Model the time evolution of the gas distribution function on both sides of a cell interface separately,take moments of the inner cell interface gas distribution function to get flow variables,and update the cell-averaged gradients of flow variables inside each control volume;4).Based on the cell-averaged flow variables and their gradients,develop compact initial data reconstruction to get initial condition of flow distributions at the beginning of next time step.A compact gas-kinetic scheme(GKS)up to sixth-order accuracy in space and fourth-order in time has been constructed on 2D unstructured *** this paper,the compact GKS up to fourth-order accuracy on three-dimensional tetrahedral mesh will be further constructed with the focus on the WENO-type initial compact data *** weights are designed to achieve high-order accuracy for the smooth Navier-Stokes solution and keep super robustness in 3D computation with strong shock *** fourth-order compact GKS uses a large time step with a CFL number 0.6 in the simulations from subsonic to hypersonic flow.A series of test cases are used to validate the *** high-order compact GKS can be used in 3D applications with complex geometry.

关键词： Compact scheme High-order GKS WENO reconstruction Tetrahedral mesh

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A Slider-Type Trim Strategy to Deal with Wing Perforation Damage Based on CFD 5th

A Slider-Type Trim Strategy to Deal with Wing Perforation Da...

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5th China aviation science and technology Conference, 2021

作者： Peng, Qiancheng Pei, Yang Li, Mingsuo Bai, Chunyu Zhang, Yu School of Aeronautics Northwestern Polytechnical University Xi’an710072 China Science and Technology on Electro-Optic Control Laboratory Luoyang471009 China Aviation Key Laboratory of Science and Technology on Structures Impact Dynamics Aircraft Strength Research Institute of China Xi’an710065 China

ISBN: (纸本)9789811674228

In this paper, a numerical simulation study is carried out on the aerodynamic characteristics of the aircraft wing surface after damage. The damage form is the wing perforation. To study the aerodynamic characteristics of the UAV under the condition of varying degrees of damage to the wings of the small airplane model, establish the geometric model of the airplane model in the CATIA 3D modeling software, and establish the geometric model in ANSYS ICEM and divide the calculation domain flow field grid. Perform aerodynamic calculations in ANSYS FLUENT. Firstly, the aerodynamic characteristics of the undamaged aircraft are calculated and analyzed, and then the aerodynamic characteristics of each damage situation are compared according to the different damage positions, and a response strategy using the slider as an auxiliary trim method is proposed. The research results have certain reference value for aircraft design of this type of layout. © 2022, The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.

关键词： Wings

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A Enhanced Feature Extraction for 3D Object Detection

A Enhanced Feature Extraction for 3D Object Detection

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System Simulation technology and its Application (CCSSTA), IEEE China Conference on

作者： Qingao Meng Jigang Tong Sen Yang Tian Xie Xin Jin The School of Electrical Engineering and Automation Tianjin University of Technology Tianjin China National Key Laboratory of Science and Technology on Aircraft Control Avic Xi’an Flight Automatic Control Research Institute Xi’an China

ISBN: (数字)9798350366600

ISBN: (纸本)9798350366617

3D object detection is crucial for autopilot and augmented reality applications. However, accurate feature extraction is the key to achieve high-precision detection, but traditional methods face the challenges of information loss and computational inefficiency. To address this, we propose an enhanced feature extraction method. We first divide the 3D space into voxel grids of varying scales. Then, using 3D sparse convolution, we extract features which are compressed along the Z axis to form BEV (Bird’s Eye View) feature images. An efficient multi-scale attention mechanism is then employed to enhance these BEV features. The refined feature map is subsequently located and classified through a CT-stacking module and RPN (Region Proposal Network). Voxel features from the proposal and 3D backbone are passed through a voxel RoI pool to directly extract RoI features from the 3D features for further refinement. Finally, a cascaded attention network refines the proposal and strengthens confidence prediction. Experiments on test set validate our method effectiveness, showing improved accuracy over traditional voxel methods. Overall, this enhanced feature extraction technique offers a promising solution for 3D target detection, particularly in scenarios demanding high real-time performance and precision.

关键词： Three-dimensional displays Accuracy Convolution Object detection Detectors Feature extraction Transformers Systems simulation Proposals Data mining

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An Optimization Method for the Swing of a Quadrotor flight Suspension System

An Optimization Method for the Swing of a Quadrotor Flight S...

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System Simulation technology and its Application (CCSSTA), IEEE China Conference on

作者： Sen Yang Xinlian Zang Jigang Tong Tian Xie Xin Jin The School of Electrical Engineering and Automation Tianjin University of Technology Tianjin China National key laboratory of science and technology on aircraft control AVIC Xi’an Flight Automatic Control Research Institute Xi‘an China

ISBN: (数字)9798350366600

ISBN: (纸本)9798350366617

The aim of this study is to explore optimization control methods for suspension systems during the flight of quadcopters. The traditional control method of suspension system has some problems such as oscillation and instability, so an optimization scheme based on Gaussian pseudo-general algorithm is proposed in this paper. Through numerical simulation and actual flight test, the effectiveness of the optimization algorithm in improving system stability and reducing oscillation amplitude is verified. At the same time, this study conducted a comparative analysis of the suspension system of the quadrotor vehicle and the free fall body, and the optimization algorithm is found to be feasible and can well improve the control accuracy and stability of the system, and provide strong support for the safety of the quadrotor vehicle in various application scenarios.

关键词： Suspensions (mechanical systems) Accuracy Stability analysis Robustness Systems simulation Safety Vehicle dynamics Oscillators Numerical stability Quadrotors

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Simulation of High Temperature Thin Film Thermocouple on Engine Blade Surface

Simulation of High Temperature Thin Film Thermocouple on Eng...

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2022 International Conference on Mechatronics and Automation technology, ICMAT 2022

作者： Zhang, Meiju Tian, Bian Ma, Rong Huang, Manguo Liang, Xiaobo Liu, Jiangjiang Zhang, Zhongkai Beijing Changcheng Aeronautic Measurement and Control Technology Research Institute Beijing101111 China Aviation Key Laboratory of Science and Technology on Special Condition Monitoring Sensor Technology Beijing101111 China State Key Laboratory for Mechanical Manufacturing Systems Engineering Xi'an Jiaotong University Xi'an710049 China

ISBN: (纸本)9781643683669

In order to avoid the instability flutter of aero-engine blade and prevent the failure of thin film thermocouple caused by the blade in complex environment, the structural strength of the thermocouple on the actual blade surface was studied in this paper. Firstly, based on the 3D scanning of the real blade, the blade model is established after the point cloud graphics. The surface thermocouple model of the blade is established in Solidworks for simulation, and the modal and harmonic response analysis of the blade is simulated. Secondly, the vibration of the curved thin film thermocouple and the stress distribution of the blade under the acceleration shock were studied in Comsol, and the failure weakness was analyzed to avoid the failure of the thin film thermocouple caused by the bending, fracture or shedding of the thin film thermocouple on the blade due to vibration and shock, providing the most suitable thermocouple selection for the engine blade. © 2022 The authors and IOS Press.

关键词： Thermocouples

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