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l_(1)-based calibration of POD-Galerkin models of two-dimensional unsteady flows

Chinese Journal of Aeronautics 2021年第1期34卷 226-236页

作者： Riccardo RUBINI davide LASAGNA andrea da ronch Faculty of Engineering and Physical Sciences University of SouthamptonSouthampton SO171BJUnited Kingdom

This paper discusses a physics-informed methodology aimed at reconstructing efficiently the fluid state of a ***,the generation of an accurate reduced order model of twodimensional unsteady flows from data leverages on sparsity-promoting statistical learning *** cornerstone of the approach is l_(1) regularised regression,resulting in sparselyconnected models where only the important quadratic interactions between modes are *** original dynamical behaviour is reproduced at low computational costs,as few quadratic interactions need to be *** approach has two key ***,interactions are selected systematically as a solution of a convex optimisation problem and no a priori assumptions on the physics of the flow are ***,the presence of a regularisation term improves the predictive performance of the original model,generally affected by noise and poor data *** cases are for two-dimensional lid-driven cavity flows,at three values of the Reynolds number for which the motion is chaotic and energy interactions are scattered across the *** is found that:(A)the sparsification generates models maintaining the original accuracy level but with a lower number of active coefficients;this becomes more pronounced for increasing Reynolds numbers suggesting that extension of these techniques to real-life flow configurations is possible;(B)sparse models maintain a good temporal stability for *** methodology is ready for more complex applications without modifications of the underlying theory,and the integration into a cyberphysical model is feasible.

关键词： Computational methods Dynamical systems Lid-driven cavity L_(1)-based regression Reduced order models Sparsification Stabilization of ROMs

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Design methodology of a mini-missile considering flight performance and guidance precision

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Journal of Systems Engineering and Electronics 2024年第1期35卷 195-210页

作者： ZHANG Licong GONG Chunlin SU Hua andrea da ronch Shaanxi Aerospace Flight Vehicle Design Key Laboratory School of AstronauticsNorthwestern Polytechnical UniversityXi’an 710072China Faculty of Engineering and Physical Sciences University of SouthamptonSouthampton SO171BJUnited Kingdom

The design of mini-missiles(MMs)presents several novel *** stringent mission requirement to reach a target with a certain precision imposes a high guidance *** miniaturization of the size of MMs makes the design of the guidance,navigation,and control(GNC)have a larger-thanbefore impact on the main-body design(shape,motor,and layout design)and its design objective,i.e.,flight *** a trade-off between flight performance and guidance precision,all the relevant interactions have to be accounted for in the design of the main body and the GNC ***,a multi-objective and multidisciplinary design optimization(MDO)is *** pertinent to motor,aerodynamics,layout,trajectory,flight dynamics,control,and guidance are included in the proposed MDO *** optimization problem seeks to maximize the range and minimize the guidance *** problem is solved by using the nondominated sorting genetic algorithm *** optimum design that balances a longer range with a smaller guidance error is ***,lessons learned about the design of the MM and insights into the trade-off between flight performance and guidance precision are given by comparing the optimum design to a design provided by the traditional approach.

关键词： mini-missiles(MMs) guidance navigation and control(GNC)system multi-objective optimization multidisciplinary design optimization(MDO) flight performance guidance precision

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A study of morphing aircraft on morphing rules along trajectory

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Chinese Journal of Aeronautics 2021年第7期34卷 232-243页

作者： Xiaoyu CHEN Chunna LI Chunlin GONG Liangxian GU andrea da ronch Shaanxi Aerospace Flight Vehicle Design Key Laboratory School of AstronauticsNorthwestern Polytechnical UniversityXi’an 710072China University of Southampton Southampton SO171BJUnited Kingdom

Morphing aircraft can meet requirements of multi-mission during the whole flight due to changing the aerodynamic shape,so it is necessary to study itsmorphing rules along the ***,trajectory planning considering morphing variables requires a huge number of expensive CFD computations due to the morphing in view of aerodynamic *** the given missions and trajectory,to alleviate computational cost and improve trajectory-planning efficiency formorphing aircraft,an offline optimizationmethod is proposed based onMulti-Fidelity Kriging(MFK)*** angle of attack,Mach number,sweep angle and axial position of the morphing wing are defined as variables for generating training data for building the MFK models,in which many inviscid aerodynamic solutions are used as low-fidelity data,while the less high-fidelity data are obtained by solving viscous *** the built MFK models of the lift,drag and pressure centre at the different angles of attack andMach numbers are used to predict the aerodynamic performance of the morphing aircraft,which keeps the optimal sweep angle and axial position of the wing during trajectory ***,themorphing rules can be correspondingly acquired along the trajectory,aswell as keep the aircraftwith the best aerodynamic performance during thewhole *** trajectory planning of amorphing aircraft was performed with the optimal aerodynamic performance based on the MFK models,built by only using 240 low-fidelity data and 110 high-fidelity *** results indicate that a complex trajectory can take advantage of morphing rules in keeping good aerodynamic performance,and the proposed method is more efficient than trajectory optimization by reducing 86%of the computing time.

关键词： Aerodynamic Morphing wing Multi-fidelity Kriging model Offline optimization Trajectory planning

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Extension of analytical indicial aerodynamics to generic trapezoidal wings in subsonic flow

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Chinese Journal of Aeronautics 2018年第4期31卷 617-631页

作者： andrea da ronch Antonino VENTURA Marcello RIGHI Matteo FRANCIOLINI Marco BERCI daniel KHARLAMOV Faculty of Engineering and the Environment University of Southampton Southampton SO17 1B J UK School of Engineering Zurich University of Applied Sciences Winterthur 8401 Switzerland Dipartimento di Ingegneria Industriale e Seienze Matematiche Universita Politecnica delle Marche Ancona 1-60100 Italy School of Mechanical Engineering University of Leeds Leeds LS2 9JT UK

Analytical indicial aerodynamic functions are calculated for several trapezoidal wings in subsonic flow, with a Mach number 0.3 Ma 0.7. The formulation herein proposed extends wellknown aerodynamic theories, which are limited to thin aerofoils in incompressible flow, to generic trapezoidal wing planforms. Firstly, a thorough study is executed to assess the accuracy and limitation of analytical predictions, using unsteady results from two state-of-the-art computational fluid dynamics solvers as cross-validated benchmarks. Indicial functions are calculated for a step change in the angle of attack and for a sharp-edge gust, each for four wing configurations and three Mach numbers. Then, analytical and computational indicial responses are used to predict dynamic derivatives and the maximum lift coefficient following an encounter with a one-minus-cosine gust. It is found that the analytical results are in excellent agreement with the computational results for all test cases. In particular, the deviation of the analytical results from the computational results is within the scatter or uncertainty in the data arising from using two computational fluid dynamics solvers. This indicates the usefulness of the developed analytical theories.

关键词： Analytical approach CFD Compressible flow Gust response Indicial aerodynamics Trapezoidal wing

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An efficient uncertainty propagation method for nonlinear dynamics with distribution-free P-box processes

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Chinese Journal of Aeronautics 2024年第12期37卷 116-138页

作者： Licong ZHANG Chunna LI Hua SU Yuannan XU andrea da ronch Chunlin GONG Flight Vehicle Design Key Laboratory School of AstronauticsNorthwestern Polytechnical UniversityXi’an 710072China Research and Development Department China Academy of Launch Vehicle TechnologyBeijing 100076China Faculty of Engineering and Physical Sciences University of SouthamptonSouthamptonEngland SO171BJUK

The distribution-free P-box process serves as an effective quantification model for timevarying uncertainties in dynamical systems when only imprecise probabilistic information is ***,its application to nonlinear systems remains limited due to excessive *** work develops an efficient method for propagating distribution-free P-box processes in nonlinear ***,using the Covariance Analysis Describing Equation Technique(CADET),the dynamic problems with P-box processes are transformed into interval Ordinary Differential Equations(ODEs).These equations provide the Mean-and-Covariance(MAC)bounds of the system responses in relation to the MAC bounds of P-box-process *** also separate the previously coupled P-box analysis and nonlinear-dynamic simulations into two sequential steps,including the MAC bound analysis of excitations and the MAC bounds calculation of responses by solving the interval ***,a Gaussian assumption of the CADET is extended to the P-box form,i.e.,the responses are approximate parametric Gaussian P-box *** a result,the probability bounds of the responses are approximated by using the solutions of the interval ***,the Chebyshev method is introduced and modified to efficiently solve the interval *** proposed method is validated based on test cases,including a duffing oscillator,a vehicle ride,and an engineering black-box problem of launch vehicle *** to the reference solutions based on the Monte Carlo method,with relative errors of less than 3%,the proposed method requires less than 0.2% calculation *** proposed method also possesses the ability to handle complex black-box problems.

关键词： Nonlinear dynamics Uncertainty propagation Imprecise probability Distribution-free P-box processes Chebyshev method

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Design optimization and testing of a morphing leading-edge with a variable-thickness compliant skin and a closed-chain mechanism

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Chinese Journal of Aeronautics 2024年第7期37卷 285-300页

作者： Zhigang WANG Xiasheng SUN Yu YANG Wenjie GE daochun LI Jinwu XIANG Panpan BAO Qi WU andrea da ronch School of Aeronautical Science and Engineering Beihang UniversityBeijing 100191China National Key Laboratory of Strength and Structural Integrity Aircraft Strength Research Institute of ChinaXi’an 710065China School of Aeronautics and Astronautics Shanghai Jiao Tong UniversityShanghai 200240China School of Mechanical Engineering Northwestern Polytechnical UniversityXi’an 710072China Faculty of Engineering and Physical Sciences University of SouthamptonSouthampton SO171JBUK

Climate warming and the increased demand in air travels motivate the aviation industry to urgently produce technological *** of the most promising innovations is based on the smoothly continuous morphing leading-edge *** study proposes a two-step process for the design of a morphing leading-edge,including the optimization of the outer variable-thickness composite compliant skin and the optimization of the inner kinematic *** the compliant skin design,an optimization of the variable thickness composite skin is proposed based on a laminate continuity model,with laminate continuity constraint and other manufacturing *** laminate continuity model utilizes a guiding sequence and a ply-drop sequence to describe the overall stacking sequence of plies in different thickness regions of the complaint *** the inner kinematic mechanism design,a coupled four-bar linkage system is proposed and optimized to produce specific trajectories at the actuation points on the stringer hats of the compliant skin,which ensures that the compliant skin can be deflected into the aerodynamically optimal ***,a morphing leading-edge is manufactured and *** results are compared with numerical predictions,confirming the feasibility of the morphing leading-edge concept and the overall proposed design approach.

关键词： Optimization Design Morphing wing Compliant skin Kinematics Leading-edge Control surfaces

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A modified airfoil-based piezoaeroelastic energy harvester with double plunge degrees of freedom

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Theoretical & Applied Mechanics Letters 2016年第5期6卷 244-247页

作者： Yining Wu daochun Li Jinwu Xiang andrea da ronch School of Aeronautic Science and Engineering Beihang University Engineering and the Environment University of Southampton

In this letter, a piezoaeroelastic energy harvester based on an airfoil with double plunge degrees of freedom is proposed to additionally take advantage of the vibrational energy of the airfoil pitch motion. An analytical model of the proposed energy harvesting system is built and compared with an equivalent model using the well-explored pitch-plunge configuration. The dynamic response and average power output of the harvester are numerically studied as the flow velocity exceeds the cut-in speed （flutter speed）. It is found that the harvester with double-plunge configuration generates 4%-10% more power with varying flow velocities while reducing 670 of the cut-in speed than its counterpart.

关键词： Energy harvesting Aeroelastic Airfoil Piezoelectric

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基于非线性涡格法的快速静气动弹性数值模拟技术

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气体物理 2020年第6期5卷 26-38页

作者：孙岩 andrea da ronch 王运涛孟德虹洪俊武许贤超中国空气动力研究与发展中心计算空气动力研究所四川绵阳621000 中国空气动力研究与发展中心空气动力学国家重点实验室四川绵阳621000 南安普顿大学物理科学与工程学院英国南安普顿SO171BJ

基于2.5D RANS数据和VLM耦合的方式,发展了一种考虑非线性流动效应的混合型涡格法HVLM.采用矩形直/后掠机翼两个外形的跨声速算例,通过与VLM、三维CFD计算数据的比较,对HVLM的气动力预测精度进行了分析与评估.对比结果表明,HVLM在大幅... 详细信息

基于2.5D RANS数据和VLM耦合的方式,发展了一种考虑非线性流动效应的混合型涡格法HVLM.采用矩形直/后掠机翼两个外形的跨声速算例,通过与VLM、三维CFD计算数据的比较,对HVLM的气动力预测精度进行了分析与评估.对比结果表明,HVLM在大幅降低时间成本的前提下可以获得和三维CFD方法预测值十分接近的计算数据,对线化VLM方法的修正效果显著.然后,HVLM与悬臂梁有限元求解耦合,实现了一种面向三维机翼的快速静气动弹性数值模拟技术,并通过矩形直机翼算例进行了验证.耦合算例的时间分析数据表明,HVLM/Beam耦合的方式能够在10 s以内完成1次三维机翼静气动弹性分析,在气动/结构耦合分析、优化设计方面展示出了良好的应用前景.

关键词： 2.5D RANS 混合型涡格法 CFD 静气动弹性悬臂梁

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Glial response in the midcingulate cortex in Huntington’s disease

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Neural Regeneration Research 2025年第1期20卷 207-208页

作者： Thulani H.Palpagama andrea Kwakowsky Center for Brain Research and Department of Anatomy and Medical Imaging Faculty of Medical and Health SciencesUniversity of AucklandAucklandNew Zealand Pharmacology and Therapeutics School of MedicineGalway Neuroscience CenterUniversity of GalwayGalwayIreland

Huntington’s disease(HD)is a genetic disease characterized by the progressive degeneration of the striatum and *** can present with a variety of symptoms that can broadly be classified into motor symptoms,inclusive of choreatic movements and rigidity,mood and psychiatric symptoms,such as depression and apathy,and cognitive symptoms,such as cognitive *** causal mutation underlying HD results from an expansion of a CAG repeat sequence on the IT15 gene,resulting in the formation and accumulation of a mutant huntingtin protein.

关键词： Huntington degeneration cortex

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Neuroinflammation as a therapeutic target in Huntington's disease

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Neural Regeneration Research 2025年第3期20卷 817-818页

作者： andrea Kwakowsky Thulani H.Palpagama Center for Brain Research and Department of Anatomy and Medical Imaging Faculty of Medical and Health SciencesUniversity of AucklandAucklandNew Zealand Pharmacology and Therapeutics School of MedicineGalway Neuroscience CentreUniversity of GalwayGalwayIreland

In 1872, George Huntington presented his essay “On Chorea” to the Meigs and Mason Academy of Medicine and, in doing so, detailed a disease that would later bear his name. Huntington's disease(HD) is a genetic, neurodegenerative disease that manifests as the loss of motor control,cognitive impairment,and mood and psychiatric changes in paents.

关键词： Huntington inflammation Medicine

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