Active Aerothermoelastic Control of

Active Aerothermoelastic Control of Hypersonic Double-wedge Lifting Surface

Designing reentry space vehicles and high-speed aireraft requires special attention to the nonlinear thermoelastic and aerodynamic instability of their structural components. The thermal effects are important since temperature environment brings dramatic influences on the static and dynamic behaviors of flight structures in supersonic/hypersonic regimes and is likely to cause instability, catastrophic failure and oscillations resulting in structural failure due to fatigue. In order to understand the dynamic behaviors of these "hot"structures, a double-wedge lifting surface with combining freeplay and cubic structural nonlinearities in both plunging and pitching degrees-of-freedom operating in supersonic/hypersonic flight speed regimes has been analyzed. A third order piston theory aerodynamic isused to estimate the applied nonlinear unsteady aerodynamic loads. Also considered is the loss of torsiunal stiffness that may be incurredby lifting surfaces subject to axial stresses induced by aerodynamic heating. The aerodynamic heating effects are estimated based on theadiabatic wall temperature due to high speed airstreams. As a recently emerging technology, the active aerothermoelastic control isaimed at providing solutions to a large number of problems involving the aeronautica Faerospace flight vehicle structures. To preventsuch damaging phenomena from occurring, an application of linear and nonlinear active control methods on both flutter boundary andpost-flutter behavior has been fulfilled. In this paper, modeling issues as well as numerical simulation have been presented and pertinent conclusions outlined. It is evidenced that a serious loss of torsional stiffness may induce the dynamic instability; however active controlcan be used to expand the flutter boundary and convert unstable limit cycle oscillations (LCO) into the stable LCO and/or to shift the transition between these two states toward higher flight Mach numbers.

作 者： Laith K Abbas Chen Qian Piergiovanni Marzocca Gürdal Zafer Abdalla Mostafa   作者單位： Laith K Abbas,Chen Qian(Institute of Vibration Engineering Research, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China)

Piergiovanni Marzocca(School of Engineering Mechanical and Aeronautical Engineering Dept. Clarkson University, Potsdam, NY13699, USA)

Gürdal Zafer,Abdalla Mostafa(Aerospace Structures, Faculty of Aerospace Engineering, Delft University of Technology, Delft 2629HS, The Netherlands) 

刊 名： 中國(guó)航空學(xué)報(bào)（英文版）  ISTIC 英文刊名： CHINESE JOURNAL OF AERONAUTICS  年，卷(期)： 2008 21(1)  分類號(hào)： V2  關(guān)鍵詞： active control   aerothermoelastic analysis   freeplay   hypersonic speed  

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