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IEEE Symposium on Intelligent Vehicle

作者： Zhipeng Shen Chao Huang Hailong Huang Yutong Wang Fei-Yue Wang Abbas Jamalipour Duc Truong Pham Ljubo Vlacic Andrey V. Savkin Department of Aeronautical and Aviation Engineering the Hong Kong Polytechnic University Hong Kong Department of Industrial and Systems Engineering the Hong Kong Polytechnic University Hong Kong State Key Laboratory for Management and Control of Complex Systems Institute of Automation Chinese Academy of Sciences Beijing China Institute of Engineering Macau University of Science and Technology Macau China School of Electrical and Information Engineering University of Sydney Sydney Australia Department of Mechanical Engineering University of Birmingham Birmingham UK Institute of Intelligent & Integrated Systems and the School of Engineering and Built Environment Griffith University Brisbane Australia School of Electrical Engineering and Telecommunications University of New South Wales Sydney Australia

ISBN: (数字)9798350348811

ISBN: (纸本)9798350348828

In this paper, we propose the innovative use of Intelligent Vehicle Carriers (IVCs) as a key solution to address the energy constraints of small-scale unmanned Intelligent Vehicles (IVs). IVCs function as both transporters and charging stations, significantly boosting the operational range and efficiency of IVs. Our research delves into the IV-IVC collaborative framework, highlighting the existing challenges, exploring potential solutions, and examining a range of applications. This study offers a visionary approach to revolutionizing intelligent transportation systems by leveraging the synergistic relationship between IVs and IVCs.

关键词： Intelligent vehicles Collaboration Charging stations Boosting

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Aerodynamic interactions of staggered counter-rotating rotor system

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Chinese Journal of Aeronautics 2025年

作者： He ZHU Yuhao DU Hong NIE Shaoxiong WEI Xiaohui WEI National Key Laboratory of Helicopter Aeromechanics Nanjing University of Aeronautics and Astronautics Nanjing 210016 China Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle Nanjing University of Aeronautics and Astronautics Nanjing 210016 China College of Aerospace Engineering Nanjing University of Aeronautics and Astronautics Nanjing 210016 China State Key Laboratory of Mechanics and Control for Aerospace Structures Nanjing University of Aeronautics and Astronautics Nanjing 210016 China

With the widespread application of Staggered Counter-rotating Rotor (SCR) systems in eVTOL and UAV configurations, a comprehensive understanding of SCR performance under Out-of-Ground Effect (OGE) and In-Ground Effect (IGE) conditions is crucial for aircraft design and landing safety. This study experimentally measured the changes in thrust and torque of the upper and lower rotors in an SCR system under varying axial and radial distances. It focuses on the interaction mechanisms between the upper and lower rotors and conducts specific IGE state experiments for certain SCR configurations. The findings reveal that changes in the lower rotor predominantly influence the overall performance of the SCR system, regardless of OGE or IGE conditions. Under OGE conditions, radial distance has a more significant impact than axial distance. Conversely, under IGE conditions, the axial distance plays a critical role in improving SCR system performance. These results provide a broad parameter range to assess SCR system performance variations, offering guidance for the design of new concept rotorcraft configurations and the development of aerodynamic prediction models under IGE conditions.

关键词： eVTOL Staggered counter-rotating rotors Aerodynamic interaction Ground effect Flow visualization Rotorcraft design

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Adaptive wave-particle decomposition in UGKWP method for high-speed flow simulations

Advances in Aerodynamics

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Advances in Aerodynamics 2023年第4期 40-65页

作者： Yufeng Wei Junzhe Cao Xing Ji Kun Xu Department of Mathematics Hong Kong University of Science and Technology School of Aeronautics Northwestern Polytechnical University Shaanxi Key Laboratory of Environment and Control for Flight Vehicle Xi'an Jiaotong University Department of Mechanical and Aerospace Engineering Hong Kong University of Science and Technology HKUST Shenzhen Research Institute

With wave-particle decomposition, a unified gas-kinetic wave-particle(UGKWP) method has been developed for multiscale flow simulations. With the variation of the cell Knudsen number, the UGKWP method captures the transport process in all flow regimes without the kinetic solver's constraint on the numerical mesh size and time step being determined by the kinetic particle mean free path and particle collision time. In the current UGKWP method, the cell Knudsen number, which is defined as the ratio of particle collision time to numerical time step, is used to distribute the components in the wave-particle decomposition. The adaptation of particles in the UGKWP method is mainly for the capturing of the non-equilibrium transport. In this aspect, the cell Knudsen number alone is not enough to identify the non-equilibrium state. For example, in the equilibrium flow regime with a Maxwellian distribution function, even at a large cell Knudsen number, the flow evolution can be still modelled by the Navier-Stokes solver. More specifically, in the near space environment both the hypersonic flow around a space vehicle and the plume flow from a satellite nozzle will encounter a far field rarefied equilibrium flow in a large computational domain. In the background dilute equilibrium region, the large particle collision time and a uniform small numerical time step can result in a large local cell Knudsen number and make the UGKWP method track a huge number of particles for the far field background flow in the original approach. But, in this region the analytical wave representation can be legitimately used in the UGKWP method to capture the nearly equilibrium flow evolution. Therefore, to further improve the efficiency of the UGKWP method for multiscale flow simulations, an adaptive UGKWP(AUGKWP) method is developed with the introduction of an additional local flow variable gradient-dependent Knudsen number. As a result, the wave-particle decomposition in the UGKWP method is determ

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Height and attitude tracking control of an unmanned helicopter via a HDOB-backstepping composite control method

Height and attitude tracking control of an unmanned helicopt...

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2019 Jiangsu Annual Conference on Automation, JACA 2019

作者： Han, Ling Wang, Xiangyu Li, Shihua Liu, Jiyu School of Automation Southeast University Nanjing210096 China Key Laboratory of Measurement and Control of Complex Systems of Engineering Ministry of Education China Aviation Key Laboratory of Science and Technology on Aircraft Control Facri Xian710065 China

This study studies the height and attitude tracking control problem of an unmanned helicopter system with disturbances. A composite controller based on the combination of harmonic disturbance observers and backstepping technique is proposed to achieve asymptotic tracking for height and attitude. Firstly, harmonic disturbance observers (HDOB) are designed to estimate the unknown disturbances affecting each channel. Then, a composite controller is proposed by integrating the backstepping control technique and the HDOB technique together to achieve the height and attitude tracking goal. Stability analysis of the closed-loop system is given. Finally, numerical simulations are presented to verify the efficiency of the proposed control scheme. © 2019 Institution of Engineering and technology. All rights reserved.

关键词： Backstepping

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Friction characteristics of hydrodynamic swashplate-bearing pair in aviation hydraulic servo motors

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Chinese Journal of Aeronautics 2025年

作者： Zhenyu WANG Xiaochao LIU Xingyu ZHOU Wenfu ZENG Weizhi QIAO Quanrun MOU Rui NIE Jing YAO School of Automation Science and Electrical Engineering Beihang University Beijing 100191 China Ningbo Institute of Technology Beihang University Ningbo 315800 China National Key Laboratory of Aircraft Integrated Flight Control Beijing 100191 China School of Mechanical Engineering Yanshan University Qinhuangdao 066000 China Schoole of Aeronautic Science and Engineering Beihang University Beijing 100191 China

Hydraulic servo motors are widely used in aircraft utility systems due to their high-efficiency bidirectional variable displacement drive characteristics. However, the displacement changes process leads to severe fric-tion losses between the swashplate and the bearing, and effective solutions are currently lacking. To address this issue, a Hydrodynamic Swashplate-Bearing Pair (HSBP) structure is proposed for hydraulic servo motors, which avoids the direct contact problem of traditional structures. A numerical calculation model for the HSBP is established, the axial displacement phenomenon generated during the reciprocating motion of the swash plate is considered, and a local mobility method is introduced to solve the frictional characteristic pa-rameters of the new friction pair. The analysis and calculation results obtained the influence law of different working condition parameters and structural parameters on the friction characteristics. A quasi-actual fric-tion test bench is developed to simulate the actual motion characteristics of the swashplate, simplifying the testing method for the friction pair. The experimental results show an error of less than 10% compared to the calculated results. Additionally, the experimental results demonstrate that the proposed hydrodynamic swashplate bearing structure can effectively reduce the friction force during the displacement adjustment process of hydraulic servo motors by more than 90% compared to traditional swashplate bearing structures.

关键词： Hydraulic motors Aircraft utility systems Hydrodynamic lubrication Swashplate-Bearing Pair Friction

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Nonlinear control Method for Hypersonic Vehicle Based on Double Power Reaching Law of Sliding Mode

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Transactions of Nanjing University of Aeronautics and Astronautics 2018年第5期35卷 849-857页

作者： Liu Rong Zhang Heng Liang Jin Key Laboratory of UAV’s Advanced Technology(Nanjing University of Aeronautics and Astronautics) Ministry of Industry and Information Technology College of Automation Engineering Nanjing University of Aeronautics and Astronautics Key Laboratory of Aircraft Control Integration Technology Aviation Industry Xi’an Flight Automatic Control Research Institute

The intelligence nonlinear control scheme via double power reaching law based sliding mode control method is proposed to solve the problems of model uncertainties and unknown outside ***,the aerodynamic parameters of the morphing vehicle are replaced with curve-fitted approximation to build the accurate model for control design in the hypersonic *** the nonlinear vehicle model is transformed into the strict feedback multi-input/multi-output nonlinear system by using the input-output feedback linearization *** the same time,the disturbance observer is used to approximate the unknown disturbance,and the sliding mode method is used to solve the problem of non-matching and ***,according to the buffeting problem in sliding mode control,the double power is *** results show that the proposed method can ensure the global stability of the closed-loop system,and has good tracking and robust performance.

关键词： hypersonic vehicle disturbance observer double power sliding mode buffeting

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Unified gas-kinetic wave-particle method for multi-scale phonon transport

arXiv

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arXiv 2025年

作者： Liu, Hongyu Yang, Xiaojian Zhang, Chuang Ji, Xing Xu, Kun Department of Mathematics Hong Kong University of Science and Technology Clear Water Bay Kowloon Hong Kong Department of Mechanical and Aerospace Engineering Hong Kong University of Science and Technology Clear Water Bay Kowloon Hong Kong Shenzhen Research Institute Hong Kong University of Science and Technology Shenzhen China Shaanxi Key Laboratory of Environment and Control for Flight Vehicle Xi’an Jiaotong University Xi’an China Institute of Energy School of Sciences Hangzhou Dianzi University Hangzhou310018 China

Over the past 7 decades, the classical Monte Carlo method has played a huge role in the fields of rarefied gas flow and micro/nano scale heat transfer, but it also has shortcomings: the time step and cell size are limited by the relaxation time and mean free path, making it difficult to efficiently simulate multi-scale heat and mass transfer problems from the ballistic to diffusion limit. To overcome this drawback, a unified gas-kinetic wave-particle (UGKWP) method is developed for solving the phonon Boltzmann transport equation (BTE) in all regimes covering both ballistic and diffusive limits. This method is built upon the space-time coupled evolution model of the phonon BTE, which provides the framework for constructing a multi-scale flux at the cell interfaces. At the same time, in order to capture non-equilibrium transport efficiently, the multi-scale flux comprises two distinct components: a deterministic part for capturing the near-equilibrium or diffusive transport and a statistical particle part for recovering non-equilibrium or ballistic transport phenomena. The UGKWP method exhibits remarkable multi-scale adaptability and versatility, seamlessly bridging the gap between the diffusive and ballistic transport phenomena. In the diffusive limit, the present method naturally converges to the Fourier’s law, with the diminishing particle contribution, whereas in the ballistic limit, the non-equilibrium flux is fully described by the free-streaming particles. This inherent adaptability not only allows for precise capturing of both equilibrium and non-equilibrium heat transfer processes but also guarantees that the model adheres strictly to the underlying physical laws in each phonon transport regime. A series of numerical tests fully demonstrate the excellent performance of the UGKWP method in all Knudsen regimes, where the time step and cell size are not constrained by the relaxation time and mean free path in the diffusive regime. The present method is an effici

关键词： Monte Carlo methods

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Effect of flight parameters on thermal performance of a hybrid air vehicle for cargo transportation

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Applied Thermal Engineering 2020年 168卷 114807-114807页

作者： Meng, Junhui Li, Moning Zhang, Lanchuan Lv, Mingyun School of Aerospace Engineering Beijing Institute of Technology Beijing100081 China Key Laboratory of Dynamics and Control of Flight Vehicle Ministry of Education Beijing100081 China School of Aeronautic Science and Engineering Beihang University Beijing100191 China

With the growth of global trade, the market of global freight transportation is increasing. Due to the combination of aerodynamic and buoyant lift, the hybrid air vehicle (HAV) is very suitable for long-distance transport of heavy loads. To achieve a long distance transportation, the HAV is designed to own large size and surface area, which causes the HAV to receive a lot of solar radiation and the resulting thermal effects have an important impact on its flight performance and safety. Meanwhile, complex configuration and solar array covered on the surface of HAV also affect its thermal performance. A co-simulation of thermal model, output power model and dynamic model of the HAV is carried out to investigate effects of flight time, location, attitude and relative wind speed on its temperature and output power during long-distance transportation across different latitudes and longitudes. The results are expected to provide references for future development of the HAV using in long-distance transport of large cargoes. © 2019 Elsevier Ltd

关键词： Solar cells

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Distributed Finite-time Formation control for Quadrotors Based on Adaptive State Observer

Distributed Finite-time Formation Control for Quadrotors Bas...

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第三十八届中国控制会议

作者： Liqian Dou Xiuyu Ma Chuang Yang Miaomiao Du Xiaoting Wang School of Electrical and Information Engineering Aviation Key Laboratory of Science and Technology on Aircraft Control

In this paper, an adaptive state observer for multiple quadrotors is designed to observe the relative state between the leader and followers. The upper bound of disturbance need not to be known in advance in the design of state observer. In the case of unknown disturbance upper bound, an adaptive disturbance observer for attitude loop is designed to estimate the complex disturbance of a quadrotor UAV, and the results of the disturbance observer are input into the controller to compensate the unknown disturbance in order to reduce the influence of these unfavorable factors on the stability of the system. In the design of attitude controller, it is difficult to obtain the derivative of desired attitude angle because of external disturbance and chattering caused by sliding mode control. Therefore, a third-order integral filter is designed between the two subsystems to estimate the desired attitude angle and its derivative, so as to avoid the influence of external interference and sliding mode chattering on the stability of the system.

关键词： Quadrotor Finite-time Formation control State observer Disturbance observer Adaptive

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A Step-Switching Coordinate Strategy for AHV-VGI Based on Nonsingular Terminal Sliding Mode control

A Step-Switching Coordinate Strategy for AHV-VGI Based on No...

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第三十八届中国控制会议

作者： Liqian Dou Miaomiao Du Yueping Wang Xiaotong Su School of Electrical and Information Engineering Aviation Key Laboratory of Science and Technology on Aircraft Control

This paper presents a step-switching coordinate strategy for Air-breathing hypersonic vehicle with variable-geometry scramjet inlet(AHV-VGI), which can improve the aerodynamic performance of hypersonic vehicle by moving the movable lip to capture more airflow. Firstly, we transform the longitudinal model of AHV-VGI into the strict feedback form and multiple nonlinear aerodynamic models are built with different elongation distance of translating cowl(EDTC). Secondly, the longitudinal model of AHV-VGI system with different EDTC is divided into the velocity subsystem and altitude subsystem, which is designed by a finite-time nonsingular terminal sliding mode control method. Then, the common Lyapunov function is constructed to prove the stability of the closed-looped switching system with the control algorithms. Finally, simulation results are provided to validate the effectiveness of these theoretical results.

关键词： AHV-VGI step-switching coordinate control nonsingular terminal sliding mode backstepping

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