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Aeroelastic Optimization of the High Aspect Ratio Wing with aileron

Computers, Materials & Continua 2022年第3期70卷 5569-5581页

作者： Mohammad Ghalandari Ibrahim Mahariq Farhad Ghadak Oussama Accouche Fahd Jarad Department of Aerospace Engineering Sharif University of TechnologyTehran11155-8639Iran College of Engineering and Technology American University of theMiddle EastKuwait Faculty of Aerospace Engineering Engineering IHUTehranIran Department of Mathematics Cankaya UniversityEtimesgutAnkaraTurkey Department of Medical Research China Medical University HospitalChina Medical UniversityTaichungTaiwan

In aircraft wings,aileron mass parameter presents a tremendous effect on the velocity and frequency of the flutter *** that purpose,we present the optimization of a composite design wing with an aileron,using machine-learning *** properties and its distribution have a great influence on the multi-variate optimization procedure,based on speed and frequency of ***,flutter speed was obtained to estimate aileron *** mass-equilibrated and other features were *** can deduced that changing the position and mass properties of the aileron are tangible following the speed and frequency of the wing *** on the proposed optimization method,the best position of the aileron is determined for the composite wing to postpone flutter instability and decrease the existed *** represented coupled aero-structural model is emerged from subsonic aerodynamics model,which has been developed using the panel method in multidimensional *** structural modeling has been conducted by finite element method,using the p-k *** fluid-structure equations are solved and the results are extracted.

关键词： Flutter speed flutter frequency composite wing aileron multi-disciplinary optimization method

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Trajectory Tracking Strategy for Gliding Hypersonic Vehicle with aileron Stuck at an Unknown Angle

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Journal of Beijing Institute of Technology 2019年第3期28卷 447-455页

作者： Haibo Ji Lei Wang School of Automation Beijing Institute of TechnologyBeijing 100081China State Key Laboratory of Intelligent Control and Decision of Complex Systems Ministry of EducationBeijing 100081China

A nonlinear robust trajectory tracking strategy for a gliding hypersonic vehicle with an aileron stuck at an unknown position is presented in this paper. First, the components of translational motion dynamics perpendicular to the velocity are derived, and then a guidance law based on a time-varying sliding mode method is used to realize trajectory tracking. Furthermore, the rotational equations of motion are separated into an actuated subsystem and an unactuated subsystem. And an adaptive time-varying sliding mode attitude controller is proposed based on the actuated subsystem to track the command attitude and the tracking performance and robustness are therefore enhanced. The proposed guidance law and attitude controller make the hypersonic vehicle fly along the reference trajectory even when the aileron is stuck at an unknown angle. Finally, a hypersonic benchmark platform is used to demonstrate the effectiveness of the proposed strategy.

关键词： trajectory tracking stuck aileron time-varying sliding mode

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Experimental validation of a new morphing trailing edge system using Price-Pa?doussis wind tunnel tests

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Chinese Journal of Aeronautics 2019年第6期32卷 1353-1366页

作者： D.COMMUNIER R.M.BOTEZ T.WONG Laboratory of Applied Research in Active Controls Avionics and AeroServoElasticity (LARCASE)ETS

This paper presents the design and manufacturing of a new morphing wing system carried out at the Laboratory of Applied Research in Active Controls, Avionics and AeroServoElasticity(LARCASE) at the ETS in Montréal. This first version of a morphing wing allows the deformation of its trailing edge, denote by Morphing Trailing Edge(MTE). In order to characterize the technical impact of this deformation, we compare its performance with that of a rigid aileron by testing in the LARCASE’s price-Pa?doussis subsonic wind tunnel. The first set of results shows that it is possible to replace an aileron by a MTE on a wing, as an improvement was observed for the MTE aerodynamic performances with respect to the aileron aerodynamic *** improvement consisted in the fact that the drag coefficient was smaller, and the lift-to-drag ratio was higher for the same lift coefficient.

关键词： Aerodynamic performances aileron Morphing wing Trailing edge Wing tunnel tests

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