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Youth Academic Annual Conference of Chinese Association of Automation (YAC)

作者： Zelin Li Yazhou Yue Yong Wang Fangfang Wu Dantao Zhang Xiangqiao Li National Key Laboratory of Science and Technology on Aircraft Control Avic Xi’An Flight Automatic Control Research Institute Xi’an China

ISBN: (数字)9798350379228

ISBN: (纸本)9798350390780

As a complex system that integrates computer science, network communication, and physical processes, it has shown huge potential in many fields. To effectively design, analyze and optimize CPS (Cyber-Physical Systems), establishing appropriate unified methods for modeling, simulation, and analysis of CPS is of crucial importance. In this paper, the concepts and characteristics of CPS are introduced, emphasizing the nature of its interdisciplinary and heterogeneous, as well as the extensive application of aviation, aerospace, vehicle, and other fields. And then existing CPS modeling methods are systematically reviewed and summarized from three perspectives: discrete modeling, continuous modeling, and advanced language modeling methods. The challenges and technical difficulties in CPS modeling process are identified, and three feasible solutions are proposed. The proposed solutions could contribute to the further study of CPS modeling.

关键词： Computer science Analytical models Automation Computational modeling Cyber-physical systems Complex systems

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A Method for Reconstructing The Shape of Wing Panels Based on Fiber Optic Sensors and Tomographic Imaging Principles 15

A Method for Reconstructing The Shape of Wing Panels Based o...

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15th IEEE Global Reliability and Prognostics and Health Management Conference, PHM-Beijing 2024

作者： Zhan, Jun Zeng, Jie Xiang, Chao Cui, Jinpeng Zeng, Cheng Zhu, Linfeng Lu, Mingyu State Key Laboratory of Mechanics and Control for Aerospace Structures Nanjing University of Aeronautics and Astronautics No. 29 Yudao Street Nanjing210016 China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing Engineering Institute of Aircraft System Jincheng AVIC Nanjing China COMAC Beijing Aircraft Technology Research Institute Changping District Xiaotangshan Future Science and Technology City Beijing102211 China

ISBN: (纸本)9798350354010

The aircraft wing structure shape reconstruction method based on discrete strain information not only provides data support for the digital collaborative health monitoring and prediction technology of wing structure but also helps to improve the aerodynamic shape and flight quality of the aircraft, achieve structural stealth, and enhance the pointing accuracy of the on-board conformal antenna. As result, a wing skin panel shape reconstruction method based on the principle of tomographic imaging and strain information perception is proposed. According to the idea of tomographic imaging, a "non-intrusive" layout form that only requires sensors to be arranged on the periphery of the monitoring area is designed, breaking through the limitation that sensors can not be arranged in the monitoring area under special working conditions. A method for constructing the deflection shape function of the wing skin panel based on the concept of synthetic curvature is proposed, solving the problem of error accumulation and elimination of deformation inversion at non-monitoring points of the measured structure caused by the uncertainty of the limited discrete layout of sensors and the choice of interpolation fitting method. On this basis, a model deformation monitoring and inversion system for wing skin panel based on fiber optic grating sensors is constructed. The experimental results show that under the single-end fixed bending and torsion working condition, the average relative error of the panel model shape reconstruction is 4.17%. Under the double-end fixed double-concentrated load working condition, the average relative error of the shape reconstruction is 8.07%. The wing deformation distribution information reconstructed by the method proposed in this paper can be mapped onto the virtual twin model of the wing, providing technical support for the safety assessment, early warning, and on-condition maintenance of the entire service life of key structures of the aircraft. © 2024

关键词： Fixed wings

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OPTIMAL DESIGN OF THERMAL MANAGEMENT SYSTEM FOR AIRBORNE DIRECTED ENERGY WEAPONS

OPTIMAL DESIGN OF THERMAL MANAGEMENT SYSTEM FOR AIRBORNE DIR...

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

作者： Liu, Yide Li, Yang Cheng, Chaoqian Zhao, Longfei School of Automation Science and Electrical Engineering Beihang University Beijing100191 China Ningbo Institute of Technology Beihang University Ningbo315800 China National Key Laboratory of Aircraft Integrated Flight Control Beijing100191 China Key Laboratory of Advanced Aircraft Utility Systems Beihang University Ministry of Industry and Information Technology China Tianmushan Laboratory Hangzhou311115 China

Next-generation aircraft will carry directed energy weapons to ensure air superiority and significantly enhance both defensive and offensive capabilities. However, these weapons face severe thermal management challenges. This paper contributes by finely analyzing the heating mechanisms of core components within directed energy weapons and proposes a thermal management solution based on pump-driven two-phase flow. The thermal flow of the chip array layout is modeled and analyzed. The cold plate structure is optimized for the best-balanced thermal resistance and pressure drop. © The Institution of Engineering & technology 2024.

关键词： Directed-energy weapons

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Long Runtime Inertial Navigation Error Correction Algorithm Based on Map Matching

Long Runtime Inertial Navigation Error Correction Algorithm ...

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International Conference on Guidance, Navigation and control, ICGNC 2024

作者： Yang, Guoliang Gao, Liu Liu, Fang Zeng, Jin Wu, Jiale Zhu, Yabo Key Laboratory of Aeronautical Science and Technology of Inertial AVIC XI’AN Flight Automatic Control Research Institute Xi’an 710076 China School of Automation Northwestern Polytechnical University Xi’an 710000 China

ISBN: (纸本)9789819622351

Inertial navigation system (INS) is not susceptible to external interference and are currently the most widely used localization method for military vehicles. However, INS relies on dead reckoning for localization, which accumulates errors during the integral and recursive solving process. In order to suppress the INS drift under long voyage, we propose a map-matching algorithm based on Hidden Markov Model (HMM) for INS data, which adopts R-Tree to store the priori map, detects the vehicle trajectory features in real time by sliding window and matches them with the priori map, and corrects the INS localization data by weighted translation vector. After the test, the algorithm can maintain stability under different road sections and vehicle speeds, and the average positioning error is reduced from 39.31 m to 16.14 m under long runtime, which comply with the requirements of military vehicle localization. © The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd. 2025.

关键词： Error correction Hidden markov model Inertial navigation system Map matching Sliding window

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An overview of large AI models and their applications

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Visual Intelligence 2024年第1期2卷 1-22页

作者： Tu, Xiaoguang He, Zhi Huang, Yi Zhang, Zhi-Hao Yang, Ming Zhao, Jian Civil Aviation Flight University of China College of Aviation Electronics and Electrical Guanghan 618307 China National Key Laboratory of Fundamental Science on Synthetic Vision Sichuan University Chengdu 610065 China Harbin Institute of Technology Harbin 150001 China EVOL Lab The Institute of AI (TeleAI) China Telecom Beijing 100033 China School of Artificial Intelligence Northwestern Polytechnical University Xi’an 710072 China

In recent years, large-scale artificial intelligence (AI) models have become a focal point in technology, attracting widespread attention and acclaim. Notable examples include Google’s BERT and OpenAI’s GPT, which have scaled their parameter sizes to hundreds of billions or even tens of trillions. This growth has been accompanied by a significant increase in the amount of training data, significantly improving the capabilities and performance of these models. Unlike previous reviews, this paper provides a comprehensive discussion of the algorithmic principles of large-scale AI models and their industrial applications from multiple perspectives. We first outline the evolutionary history of these models, highlighting milestone algorithms while exploring their underlying principles and core technologies. We then evaluate the challenges and limitations of large-scale AI models, including computational resource requirements, model parameter inflation, data privacy concerns, and specific issues related to multi-modal AI models, such as reliance on text-image pairs, inconsistencies in understanding and generation capabilities, and the lack of true “multi-modality”. Various industrial applications of these models are also presented. Finally, we discuss future trends, predicting further expansion of model scale and the development of cross-modal fusion. This study provides valuable insights to inform and inspire future future research and practice. © The Author(s) 2024.

关键词： Artificial intelligence GPT Large AI models Large language models

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Geometric Feature-Based Airport Runway Line Detection

Geometric Feature-Based Airport Runway Line Detection

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International Conference on Guidance, Navigation and control, ICGNC 2024

作者： Liang, Yu National Key Laboratory of Science and Technology On Integrated Technology Control Flight Automatic Control Research Institute Xi’an710065 China AVIC Beijing100083 China

ISBN: (纸本)9789819622313

This paper introduces an algorithm that uses visual features for detecting airport runway lines. The purpose is to enable autonomous landing of unmanned aerial vehicles in the case of GPS denial, by providing runway line recognition, detection, and positioning information for the aircraft. The method uses Sobel edge detection and Hough transformation algorithms. First, it performs rough positioning of the left and right runway lines using high-level semantic understanding of the runway. Then, under the constraints of the left and right runway lines, it performs precise detection of the middle virtual lines. The article verifies the effectiveness and feasibility of the method with certain lighting conditions through experiments. Since the algorithm is based on traditional geometric information for runway line detection, it does not require expensive GPU training and reduces costs. © The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd. 2025.

关键词： Hough transforms

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A Review of Aircraft Ground Taxi control Techniques

A Review of Aircraft Ground Taxi Control Techniques

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

作者： Li, Bingyu Liu, Xiaochao School of Automation Science and Electrical Engineering Beihang University Beijing100191 China National Key Laboratory of Aircraft Integrated Flight Control Beihang University Beijing100191 China Key Laboratory of Advanced Aircraft Systems Beihang University Ministry of Industry and Information Technology Beijing100191 China Ningbo Institute of Technology Beihang University Ningbo315800 China Tianmushan Laboratory Hangzhou310023 China

The extensive utilization of aircraft as a mode of transportation and the accelerated expansion of the aviation market have imposed heightened expectations on airport scheduling capabilities. To enhance the efficacy of aircraft ground operations and diminish the duration of runway occupation, the analysis of aircraft motion characteristics and the management of their ground taxiing trajectories assume greater significance. This paper provides an overview of aircraft ground taxiing control technology. This paper provides a brief overview of the key parameters and trajectory prediction methods involved in the aircraft landing process. The nonlinear analysis theory is employed to introduce the aircraft brake system stability and heading stability. Subsequently, the results of significant research on ground skidding control laws are presented. The fourth section presents a summary of the issues and technological developments in aircraft ground skid run control and outlines future research priorities in anti-skid brake control. © The Institution of Engineering & technology 2024.

关键词： AIRCRAFT GROUND TAXI NONLINEAR control STABILITY ANALYSIS TRAJECTORY PREDICTION

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Physical Cross-Sectional Area Modeling of Complex Structural Spacecraft for Long-term Precision Orbit Determination 73

Physical Cross-Sectional Area Modeling of Complex Structural...

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73rd International Astronautical Congress, IAC 2022

作者： Yang, Cheng Chen, Guang-Ming Li, Rui-Long Li, Xie Luo, Yi-Hong Sun, Jun Cai, Jun-Wu Beijing Aerospace Control Center Beijing100094 China National Key Laboratory of Science and Technology on Aerospace Flight Dynamics Beijing100094 China National Key Laboratory of Aerospace Flight Dynamics Northwestern Polytechnical University Xi'an China

Atmosphere drag modeling is the greatest uncertainty in the dynamics of low Earth satellite orbits, which mainly contains the ballistic coefficient, atmosphere density and the cross-sectional area. For complex structural spacecraft, the cross-sectional area varies in a wide range according to the attitude or movable components, such as solar arrays. The residual error can't be absorbed completely by estimation of the ballistic coefficient. This paper investigates the modeling and calculation of accuracy cross-sectional area of complex structural spacecraft, and applies the method to long-term precision orbit determination. First, a scheme for approximating the accuracy module contour of any complex spacecraft by triangular meshes is developed, which can be easily generated by 3d processing software. The tree structure is employed to integrate all the meshes to a combinant according to their hierarchical relationship and motion links. By this strategy, the out surface of transformed spacecraft can be represented with the motion status of moveable modules. Then, a computer graphical approach is proposed to calculate the cross-sectional area rapidly. The projected direction can be obtained by the attitude from the telemetry data or the attitude control mode. The shadow of the spacecraft can be generated by projecting the meshes using the principle and toolkit in the computer graphic, which can imply the cross-sectional area. The method also accounts for overlaps among projections, module motion, attitude change, and is capable of providing the true area in a computationally-efficient manner. This method can be generalized to satellites of arbitrary shape. The model was applied to orbit determination of Tiangong spacecraft, and the 30-days position predicting residuals is reduced by 4%. © 2022 International Astronautical Federation, IAF. All rights reserved.

关键词： Orbits

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

Trajectory Optimization and Control Algorithm of Perch Landi...

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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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MODELING AND ANALYSIS OF ELECTRO-HYDROSTATIC ACTUATORS EFFICIENCY 34th

MODELING AND ANALYSIS OF ELECTRO-HYDROSTATIC ACTUATORS EFFIC...

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34th Congress of the International Council of the Aeronautical sciences, ICAS 2024

作者： Jiang, Chaofan Shang, Yaoxing Yu, Tian Liu, Zhicheng Li, Mingyang School of Automation Science and Electrical Engineering Beihang University Beijing China National Key Laboratory of Aircraft Integrated Flight Control Beihang University Beijing China Ningbo Institute of Technology Beihang University Ningbo China Tianmushan Laboratory Yuhang District Xixi Octagon City Hangzhou China

Electro-hydrostatic Actuator (EHA) is an important part which is used to control the control surface of aircraft. EHA has the advantage of higher efficiency compared with traditional hydraulic system. Compared with the hydraulic actuator, EHA adds motor, hydraulic pump, booster tank and other components. Therefore, the calculation of EHA efficiency is also more complex than that of hydraulic actuators. After research and analysis, the efficiency of wet motor-pump is low under large load or high speed. Using a passive load-sensitive EHA configuration can improve this situation. The motor copper loss can be reduced by reducing the displacement of piston pump under large load. But the displacement cannot be reduced blindly, which will lead to dynamic decline. The influence of displacement change velocity on dynamic and energy loss was studied. The effects of load sensitive variable displacement mechanism parameters such as piston area, spring stiffness, radius of damping hole and initial pressure on the velocity of displacement change were studied. The influence of parameters on dynamics and energy loss is obtained. So in order to balance efficiency and dynamics, particle swarm optimization method is adopted. Piston area, spring stiffness, radius of damping hole and initial pressure of variable displacement are taken as optimization variables. Energy loss and step response risetime are taken as optimization objectives. The energy loss and risetime are kept at a low level by obtaining appropriate load sensing mechanism parameters. The results show that the passive load sensing mechanism parameters obtained by particle swarm optimization algorithm can reduce the energy consumption of EHA under large load conditions and improve the efficiency of EHA without reducing the dynamic of EHA. © 2024, International Council of the Aeronautical sciences. All rights reserved.

关键词： Aircraft hydraulic systems

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