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Friction compensation for low velocity control of hydraulic flight motion simulator: A simple adaptive robust approach

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Chinese Journal of Aeronautics 2013年第3期26卷 814-822页

作者： Yao Jianyong Jiao Zongxia Han Songshan School of Mechanical Engineering Nanjing University of Science and Technology Science and Technology on Aircraft Control Laboratory Beihang University

Low-velocity tracking capability is a key performance of flight motion simulator （FMS）, which is mainly affected by the nonlinear friction force. Though many compensation schemes with ad hoc friction models have been proposed, this paper deals with low-velocity control without friction model, since it is easy to be implemented in practice. Firstly, a nonlinear model of the FMS middle frame, which is driven by a hydraulic rotary actuator, is built. Noting that in the low velocity region, the unmodeled friction force is mainly characterized by a changing-slowly part, thus a simple adaptive law can be employed to learn this changing-slowly part and compensate it. To guarantee the boundedness of adaptation process, a discontinuous projection is utilized and then a robust scheme is proposed. The controller achieves a prescribed output tracking transient performance and final tracking accuracy in general while obtaining asymptotic output tracking in the absence of modeling errors. In addition, a saturated projection adaptive scheme is proposed to improve the globally learning capability when the velocity becomes large, which might make the previous proposed projection-based adaptive law be unstable. Theoretical and extensive experimental results are obtained to verify the high-performance nature of the proposed adaptive robust control strategy.

关键词： Adaptive control Backstepping Flight motion simulator Friction compensation Hydraulic actuator Robust control

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Optimization of High-Speed WIG Airfoil with Consideration of Non-ground Effect by a Two-Step Deep Learning Inverse Design Method

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Transactions of Nanjing University of Aeronautics and Astronautics 2025年第1期42卷 56-69页

作者： WANG Chenlu SUN Jianhong ZHENG Daren SUN Zhi ZUO Si LIU Hao LI Pei Key Laboratory of Aircraft Environment Control and Life Support Ministry of Industry and Information TechnologyNanjing University of Aeronautics and AstronauticsNanjing 210016P.R.China Key Laboratory of Civil Aviation Emergency Science&Technology Civil Aviation Administration of ChinaNanjing University of Aeronautics and AstronauticsNanjing 211106P.R.China State Key Laboratory of Mechanics and Control for Aerospace Structures Nanjing University of Aeronautics and AstronauticsNanjing 210016P.R.China

Under complex flight conditions,such as obstacle avoidance and extreme sea state,wing-in-ground(WIG)effect aircraft need to ascend to higher altitudes,resulting in the disappearance of the ground effect.A design of high-speed WIG airfoil considering non-ground effect is carried out by a novel two-step inverse airfoil design method that combines conditional generative adversarial network(CGAN)and artificial neural network(ANN).The CGAN model is employed to generate a variety of airfoil designs that satisfy the desired lift-drag ratios in both ground effect and non-ground effect ***,the ANN model is utilized to forecast aerodynamic parameters of the generated *** results indicate that the CGAN model contributes to a high accuracy rate for airfoil design and enables the creation of novel airfoil ***,it demonstrates high accuracy in predicting aerodynamic parameters of these airfoils due to the ANN *** method eliminates the necessity for numerical simulations and experimental testing through the design procedure,showcasing notable *** analysis of airfoils generated by the CGAN model shows that airfoils exhibiting high lift-drag ratios under both flight conditions typically have cambers of among[0.08c,0.105c],with the positions of maximum camber occurring among[0.35c,0.5c]of the chord length,and the leading-edge radiuses of these airfoils primarily cluster among[0.008c,0.025c]

关键词： conditional generative adversarial network(CGAN) artificial neural network(ANN) airfoil design wing-in-ground(WIG)aircraft ground effect

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Assessment of recent empirical wall-pressure auto-spectrum models under various pressure gradient conditions

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Applied Mathematical Modelling 2025年 146卷

作者： Jin, Yao Li, Yaqing Liao, Fei Cai, Jinsheng School of Building Services Science and Engineering Xi'an University of Architecture and Technology Xi'an710055 China School of Aeronautics Northwestern Polytechnical University Xi'an710072 China National Key Laboratory of Aircraft Configuration Design Xi'an710072 China Laboratory of Aerodynamic Noise Control China Aerodynamics Research and Development Center Mianyang621000 China Beijing Institute of Astronautical Systems Engineering Beijing100076 China

A comprehensive comparison of twelve empirical wall-pressure auto-spectrum models developed between 1976 and 2024 is conducted to evaluate their capability and robustness in capturing spectra across a wide range of frequencies. The study collects 59 dataset pairs from public literature, covering a broad range of pressure gradient and Reynolds number conditions. Results indicate that Shubham's gene-expression-programming (GEP) model (2024) performs well in capturing low-frequency content under adverse pressure gradients, but struggles to model high-frequency roll-off decay (ω−5) under near-zero pressure gradients. Conversely, the Lee's model (2018) demonstrates satisfactory high-frequency performance but exhibits a steeper-than-expected low-frequency scaling (ω2, deviating significantly from ω0.5∼1.2). To address these limitations, a tailored sigmoid weighting technique is proposed to combine the strengths of Lee's and Shubham's models. A smooth transition between two models occurs automatically, with the critical frequency determined by RT. The resulting weighted model achieves accurate predictions across both low- and high-frequency regions. Additionally, a sensitivity analysis is performed to explore the influence of model parameters on spectra behavior. Notably, Zagarola and Smits's pressure gradient parameter (Δδ/δ⁎) exhibits distinct behaviors in the Lee's and Shubham's models, while Clauser's equilibrium parameter (βθ,δ) displays similar trends in both. Furthermore, the Lee's model provides a more intuitive and reliable interpretation of the parameter RT, capturing the Reynolds number effect effectively, compared to Shubham's GEP model. Despite its limitations, the GEP model demonstrates promise by leveraging large datasets and uncovering obscure scaling laws through machine learning techniques. Further work should focus on refining parameter roles to align more closely with physical intuition, enhancing the models' interpretability and applicability. © 2025 E

关键词： Pressure gradient

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Decoupling Trajectory Tracking for Gliding Reentry Vehicles

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IEEE/CAA Journal of Automatica Sinica 2015年第1期2卷 115-120页

作者： Zixuan Liang Zhang Ren Xingyue Shao the Science and Technology on Aircraft Control Laboratory Beihang University

A decoupling trajectory tracking method for gliding reentry vehicles is presented to improve the reliability of the guidance system. Function relations between state variables and control variables are analyzed. To reduce the coupling between control channels, the multiple-input multiple-output (MIMO) tracking system is separated into a series of two single-input single-output (SISO) subsystems. Tracking laws for both velocity and altitude are designed based on the sliding mode control (SMC). The decoupling approach is verified by the Monte Carlo simulations, and compared with the linear quadratic regulator (LQR) approach in some specific conditions. Simulation results indicate that the decoupling approach owns a fast convergence speed and a strong anti-interference ability in the trajectory tracking. © 2014 Chinese Association of Automation.

关键词： Airships Altitude control Channel estimation Hypersonic vehicles Intelligent systems MIMO systems Monte Carlo methods Sliding mode control Telecommunication repeaters Trajectories Vehicles

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Design and Flight Test of a Compact and Rapidly-Deployable Air-Launched Inflatable-Winged aircraft

Design and Flight Test of a Compact and Rapidly-Deployable A...

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AIAA science and technology Forum and Exposition, AIAA SciTech Forum 2025

作者： Ge, Hang Xu, Yixiang Sun, Donglei Chen, Xinmin Chen, Boyang School of Aerospace Faculty of Science and Engineering University of Nottingham Ningbo China Zhejiang Ningbo315100 China Department of Mechanical Materials and Manufacturing Engineering UNNC-NFTZ Blockchain Laboratory University of Nottingham Ningbo China Zhejiang Ningbo315100 China Advanced Intelligent Manufacturing Research Group Control System Lab University of Nottingham Ningbo China Zhejiang Ningbo315100 China Zhejiang Provincial Engineering Research Center of Special Aircraft Ningbo Institute of Materials Technology & Engineering Chinese Academy of Sciences Zhejiang Ningbo315100 China

ISBN: (数字)9781624107238

ISBN: (纸本)9781624107238

In this research, a high-altitude, compact and rapidly deployable, air-launched, inflatablewinged aircraft is designed, developed, and flight-tested to investigate the flight characteristics of inflatable-winged aircraft as well as the in-flight inflation and dynamic deployment properties when launched from various carriers. To start with, two types of inflatable wings employing different materials have been designed, fabricated, and tested, the tests including structural characteristics tests, inflation properties tests, and low-Reynolds-number wind-tunnel tests. A full-scale 30-kilogram prototype unmanned aerial vehicle with inflatable wings was then designed, assembled and tested with some basic low-altitude flights to verify the feasibility of the aerodynamic layout and the trim and stability and control characteristics. Finally, low- and high-altitude in-flight launches will be conducted to study the dynamic deployment properties and high-altitude flight characteristics of this design. © 2025, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： Wind tunnels

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Fully autonomous flying: from collective motion in bird flocks to unmanned aerial vehicle autonomous swarms

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science China(Information sciences) 2015年第12期58卷 211-213页

作者： QIU HuaXin WEI Chen DOU Rui ZHOU ZiWei Science and Technology on Aircraft Control Laboratory School of Automation Science and Electrical EngineeringBeihang University

1 Introduction The unmanned aerial vehicle(UAV),an aircraft with no pilots on board,appeals to widespread applications in military and civil fields[1].In complex and dynamic mission environments,a single UAV will

关键词： UAV Fully autonomous flying from collective motion in bird flocks to unmanned aerial vehicle autonomous swarms

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Theoretical study of flow ripple for an aviation axial-piston pump with damping holes in the valve plate

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Chinese Journal of Aeronautics 2014年第1期27卷 169-181页

作者： Guan Changbin Jiao Zongxia He Shouzhan School of Automation Science and Engineering Beihang University Beijing Institute of Control Engineering Science and Technology on Aircraft Control Laboratory Beihang University

Based on the structure of a certain type of aviation axial-piston pump＇s valve plate which adopts a pre-pressurization fluid path （consisting a damping hole, a buffer chamber, and an orifice） to reduce flow ripple, a single-piston model of the aviation axial-piston pump is presented. This sin- gle-piston model comprehensively considers fluid compressibility, orifice restriction effect, fluid resistance in the capillary tube, and the leakage flow. Besides, the instantaneous discharge areas used in the single-piston model have been calculated in detail. Based on the single-piston model, a multi-piston pump model has been established according to the simple hydraulic circuit. The sin- gle- and multi-piston pump models have been realized by the S-function in Matlab/Simulink. The developed multi-piston pump model has been validated by being compared with the numerical result by computational fluid dynamic （CFD）. The effects of the pre-pressurization fluid path on the flow ripple and the instantaneous pressure in the piston chamber have been studied and opti- mized design recommendations for the aviation axial-piston pump have been given out.

关键词： Axial-piston pump Damping hole Flow ripple Mathematical models Simulation Swash plate

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An algorithm for terrain-aided inertial navigation based on nonlinear optimal filtering

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science China(Physics,Mechanics & Astronomy) 2011年第6期54卷 1083-1088页

作者： ZHAO Long Science and Technology on Aircraft Control Laboratory Beihang UniversityBeijing 100191China

When the initial position error or the altimeter measurement noise is large,the BUAA Inertial Terrain-Aided Navigation (BITAN) algorithm based on extended Kalman filtering can not be located *** solve this problem,we propose a modified BITAN algorithm based on nonlinear optimal *** posterior probability density correction is obtained by using the prior probability density of the system's state transition model and the most recent ***,the local unobservable system caused by the measurement equation through terrain linearization is *** algorithm is tested by using the digital elevation model and flight data,and is compared with *** show that the accuracy of the proposed algorithm is higher than BITAN,and the robustness of the system is improved.

关键词： navigation inertial navigation terrain-aided navigation robust adaptive filtering

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Flow field and pressure loss analysis of junction and its structure optimization of aircraft hydraulic pipe system

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Chinese Journal of Aeronautics 2013年第4期26卷 1080-1092页

作者： Li Xin Wang Shaoping School of Automation Science and Electric Engineering Beihang University Science and Technology on Aircraft Control Laboratory Beihang University

The flow field in junction is complicated due to the ripple property of oil flow velocity and different frequencies of two pumps in aircraft. In this study, the flow fields of T-junction and Y-junction were analyzed using shear stress transport （SST） model in ANSYS/CFX software. The simulation results identified the variation rule of velocity peak in T-junction with different frequencies and phase-differences, meanwhile, the eddy and velocity shock existed in the corner of the T-junction, and the limit working state was obtained. Although the eddy disappeared in Y-junction, the velocity shock and pressure loss were still too big. To address these faults, an arc-junction was designed. Based on the flow fields of arc-junction, the eddy in the junction corner disappeared and the maximum of velocity peak declined compared to T-and Y-junction. Additionally, 8 series of arc-junction with different radiuses were tested to get the variation rule of velocity peak. Through the computation of the pressure loss of three junctions, the arc-junction had a lowest loss value, and its pressure loss reached the minimum value when the curvature radius is 35.42 mm, meanwhile, the velocity shock has decreased in a low phase.

关键词： Arc-junction Computational fluid dynam- ics Pipe flow Pressure loss T-junction Velocity shock Y-junction

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Feedback control design with vibration suppression for flexible air-breathing hypersonic vehicles

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science China(Information sciences) 2014年第3期57卷 249-262页

作者： GAO Yan WU HuaiNing WANG JunWei GUO Lei Science and Technology on Aircraft Control Laboratory School of Automation Science and Electrical EngineeringBeihang University

This paper investigates the problem of feedback control design with vibration suppression for a flexible air-breathing hypersonic vehicle(FAHV).FAHV includes intricate coupling between the engine and flight dynamics,as well as complex interplay between flexible and rigid modes,which results in an intractable system for the control *** this paper,a longitudinal model,which is described by a coupled system of ordinary diferential equations(ODEs)and partial diferential equations(PDEs),is ***,a linearized ODE model for the rigid part is established around the trim condition,while vibration of the fuselage is described by ***,based on the Lyapunov direct method,a control law via ODE state feedback and PDE boundary output feedback is designed for the system such that the closed-loop exponential stability is ***,simulation results are given to illustrate the efectiveness of the proposed design method.

关键词： flexible air-breathing hypersonic vehicle(FAHV) Euler-Bernoulli beam vibration suppression Lyapunov direct method boundary control

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