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Flatness-Based Control in Successive Loops for Unmanned Aerial Vehicles and Micro-Satellites

Guidance, Navigation and Control 2023年第4期3卷 26-57页

作者： Gerasimos Rigatos Masoud Abbaszadeh Krishna Busawon laurent dala Unit of Industrial Automation Industrial Systems Institute 26504 Rion Patras Greece Department of ECSE Rensselaer Polytechnic Institute 12065New YorkUSA Nonlinear Control Group University of Northumbria Newcastle NE18STUK Department of Mechanical Engineering University of Northumbria Newcastle NE18ST UK

The control problem for the multivariable and nonlinear dynamics of unmanned aerial vehicles and micro-satellites is solved with the use of a flatness-based control approach which is implemented in successive *** state-space model of(i)unmanned aerial vehicles and(ii)micro-satellites is separated into two subsystems,which are connected between them in cascading *** one of these subsystems can be viewed independently as a differentially flat system and control about it can be performed with inversion of its dynamics as in the case of input–output linearized flat *** state variables of the second subsystem become virtual control inputs for the first *** turn,exogenous control inputs are applied to the first *** whole control method is implemented in two successive loops and its global stability properties are also proven through Lyapunov stability *** validity of the control method is confirmed in two case studies:(a)control and trajectories tracking for the autonomous octocopter,(ii)control of the attitude dynamics of micro-satellites.

关键词： Autonomous octocopter attitude dynamics of micro-satellites multivariable control differential flatness properties flatness-based control in successive loops global stability Lyapunov analysis

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带有背景波系的隔离段内激波串自激振荡的实验研究与分析

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Journal of Zhejiang University-Science A(Applied Physics & Engineering) 2020年第8期21卷 614-635页

作者： Wen-xin HOU Jun-tao CHANG Chen KONG Wen BAO laurent dala School of Energy Science and Engineering Harbin Institute of TechnologyHarbin 150001China Department of Mechanical and Construction Engineering Northumbria UniversityNewcastle upon TyneNE18STUK

目的:隔离段内存在背景波系时,激波串在自激振荡过程中会出现三种振荡模式,并表现出非对称结构。本文旨在研究背景波系是如何引起激波串的非对称结构以及背景波系对振荡特性的影响,并探究自激振荡的扰动来源。创新点:1.从激波串结构和... 详细信息

目的:隔离段内存在背景波系时,激波串在自激振荡过程中会出现三种振荡模式,并表现出非对称结构。本文旨在研究背景波系是如何引起激波串的非对称结构以及背景波系对振荡特性的影响,并探究自激振荡的扰动来源。创新点:1.从激波串结构和振荡特性两个方面揭示背景波系对激波串自激振荡的影响;2.获得引起激波串自激振荡的扰动来源。方法:1.通过实验分析,结合激波极曲线,研究背景波系引起的压力间断对激波串结构的影响;2.结合实验获得的激波串振荡特性以及数值模拟得到的壁面压力梯度,分析背景波系引起的压力梯度对自激振荡的影响;3.通过对壁面压力进行相关性分析和相位分析,获得自激振荡扰动的来源。结论:1.背景波系引起的压力间断导致了激波串的非对称结构;2.背景波系引起的壁面压力梯度影响激波串前缘的振荡范围和振荡强度;3.在带有背景波系的隔离段内,引起自激振荡的扰动来源于前缘激波产生的分离区内。

关键词：自激振荡背景波系非对称结构扰动源

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Real-Time Control of the Heating of an Airfoil

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材料科学与工程（中英文A版） 2012年第5期2卷 478-487页

作者： Frangoise Masson Francisco Chinesta Adrien Leygue Elias Cueto laurent dala Craig Law EADS Corporate Foundation International Chair GEM UMR CNRS-Ecole Centrale Nantes 1 Rue de la No~ BP 92101 F-44321Nantes Cedex 3 France Institut Universitaire de France (IUF) Aragon Institute of Engineering Research-I3A Universidad de Zaragoza Maria de Luna 7 E-50018 Zaragoza Spain School of Mechanical Industrial and Aeronautical Engineering University of the Witwatersrand 1 Jan Smut Avenue SA-2000Braamfontein Johannesburg South Africa

This paper concerns the real time control of the boundary layer on an aircraft wing. This new proposed approach is associated with the unsteady surface heating regime using electrically resistant strips which are embedded in the wing skin. The control of the boundary layer separation and transition will provide a reduction in friction drag and hence a reduction in the fuel consumption. Active thermal control consists in applying the required thermal power in the different strips in order to ensure the desired temperatures on the aircraft wing. The heating being unsteady, and, as during a flight the flow conditions or the ambient temperatures vary, the thermal power changes and must be chosen as fast as possible in order to ensure optimal operating conditions. To ensure the real-time response, an original modeling considering materials and process parameters as extra-coordinates are proposed, and then the associated parametric solution is computed by solving the resulting multidimensional models by applying the proper generalized decomposition (PGD) method that allows circumventing the curse of dimensionality that multidimensional models imply.

关键词：实时控制边界层分离暖气翼型飞机机翼加热制度温度变化多维模型

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Numerical Tools for the Control of the Unsteady Heating of an Airfoil

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Journal of Mechanics Engineering and Automation 2013年第6期3卷 339-351页

作者： Franqoise Masson Francisco Chinesta Adrien Leygue Chady Ghnatios Elias Cueto laurent dala Craig Law EADS Corporate Foundation International Chair GEM UMR CNRS- Ecole Centrale Nantes F-44321 Nantes Cedex 3 France lnstitut Universitaire de France Paris 75 000 France Aragon Institute of Engineering Research - 13A Universidad de Zaragoza Zaragoza E-50018 Spain School of Mechanical Industrial and Aeronautical Engineering University of the Witwatersrand Johannesburg 2000 SouthAfrica

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