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Theoretical investigation of shock stand-off distance for non-equilibrium flows over spheres

Chinese Journal of Aeronautics 2018年第5期31卷 990-996页

作者： Hua SHEN Chih-Yung WEN Extreme Computing Research Center Computer Electrical and Mathematical Science and Engineering DivisionKing Abdullah University of Science and Technology Department of Mechanical Engineering The Hong Kong Polytechnic University

We derived a theoretical solution of the shock stand-off distance for a non-equilibrium flow over spheres based on Wen and Hornung＇s solution and Olivier＇s solution. Compared with previous approaches, the main advantage of the present approach is allowing an analytic solution without involving any semi-empirical parameter for the whole non-equilibrium flow regimes. The effects of some important physical quantities therefore can be fully revealed via the analytic solution. By combining the current solution with Ideal Dissociating Gas（IDG） model, we investigate the effects of free stream kinetic energy and free stream dissociation level（which can be very different between different facilities） on the shock stand-off distance.

关键词： Gas dynamics supersonic/hypersonic flow Shock stand-off distant Non-equilibrium flow Blunt body Shock

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Active control of supersonic/hypersonic aeroelastic flutter for a two-dimensional airfoil with flap

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Science China(Technological Sciences) 2011年第8期54卷 1943-1953页

作者： ZHAO Na School of Astronautics Harbin Institute of Technology PO Box 137 Harbin 150001 China

The flutter, post-flutter and active control of a two-dimensional airfoil with control surface operating in supersonic/hypersonic flight speed regions are investigated in this paper. A three-degree-of-freedom dynamic model is established, in which both the cubic nonlinear structural stiffness and the nonlinear aerodynamic load are accounted for. The third order Piston Theory is employed to derive the aerodynamic loads in the supersonic/hypersonic airflow. Nonlinear flutter happens with a phenomenon of limit cycle oscillations (LCOs) when the flight speed is less than or greater than linear critical speed. The LQR approach is employed to design a control law to increase both the linear and nonlinear critical speeds of aerodynamic flutter, and then a combined control law is proposed in order to reduce the amplitude of LCOs by adding a cubic nonlinear feedback control. The dynamic responses of the controlled system are given and used to compare with those of the uncontrolled system. Results of simulation show that the active flutter control method proposed here is effective.

关键词： flutter/post flutter active control supersonic/hypersonic flow 2-D airfoil nonlinearity

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ACTIVE CONTROL OF AEROELASTIC FLUTTER FOR A NONLINEAR AIRFOIL WITH FLAP

ACTIVE CONTROL OF AEROELASTIC FLUTTER FOR A NONLINEAR AIRFOI...

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第十三届全国非线性振动暨第十届全国非线性动力学和运动稳定性学术会议

作者：赵娜曹登庆龙钢 School of Astronautics Harbin Institute of Technology No.203 Research Institute of China Ordnance Industries

The flutter,post-flutter and active control of a two-dimensional airfoil with control surface operating in supersonic/hypersonic flight speed regions is investigated in this paper.A two-degree-of-freedom dynamic model is established,in which both the cubic nonlinear structural stiffness and the nonlinear aerodynamic load are accounted *** third order Piston Theory is employed to derive the aerodynamic loads in the supersonic/hypersonic *** flutter happens with a phenomenon of limit cycle oscillations(LCOs)when the flight speed is less than or greater than linear critical *** flutter boundary of supersonic/hypersonic airfoil is studied over a range of nonlinear *** LQR approach is employed to design a control law to increase both the linear and nonlinear critical speed of aerodynamic flutter,and then a combined control law is proposed in order to reduce the amplitude of LCOs by adding a cubic nonlinear feedback *** and numerical simulation methods are used to predict the flutter characteristics of the airfoil with/without *** dynamic responses of the controlled system are given and used to compare with those of the uncontrolled *** of simulation show that the active flutter control method proposed here is effective.

关键词： Flutter/post flutter active control supersonic/hypersonic flow 2-D airfoil,nonlinearity

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