高超声速飞行器空气舵系统耦合特性分析及颤振抑制研究
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摘要
为了预防高超声速飞行器空气舵系统流、固、热、电、磁等多物理场的耦合作用所引发颤振失稳开展颤振抑制研究,建立了将热环境下舵面结构动力特性、高超声速非定常气动力、舵机环节非线性动力学特性耦合起来的舵机-舵面耦合系统数学模型和颤振特性分析方法;对某舵系统进行了数值分析,研究了热环境、电动舵机设计参数以及指令信号幅值对颤振速度的影响,提出在舵机电流环加入超前滞后环节的颤振抑制措施。仿真结果表明,该方法能有效地提高舵系统的颤振速度。
The actuator-fin system of hypersonic vehicles contains the interaction between aero-dynamics, structural dynamics,thermal effects and electromagnetism, which may induce flutter instability. The mathematical model of the actuator-fin system is modeled, which couples structural dynamics of fin under the thermal circumstance with hypersonic unsteady dynamics and nonlinear dynamics of actuator, and the flutter analysis approach is presented. Numerical analysis is conducted for the actuator-fin system of a hypersonic vehicle, and the influences of the thermal circumstances, design parameters of the electromechanical actuator and amplitudes of the command signals on the flutter boundary is studied. A new method for flutter suppression is presented, which makeup a leading-lag model on the current loop of actuator. The numerical simulation shows that the method can effectively increase the flutter velocity of the actuator-fin system.
The actuator-fin system of hypersonic vehicles contains the interaction between aero-dynamics, structural dynamics,thermal effects and electromagnetism, which may induce flutter instability. The mathematical model of the actuator-fin system is modeled, which couples structural dynamics of fin under the thermal circumstance with hypersonic unsteady dynamics and nonlinear dynamics of actuator, and the flutter analysis approach is presented. Numerical analysis is conducted for the actuator-fin system of a hypersonic vehicle, and the influences of the thermal circumstances, design parameters of the electromechanical actuator and amplitudes of the command signals on the flutter boundary is studied. A new method for flutter suppression is presented, which makeup a leading-lag model on the current loop of actuator. The numerical simulation shows that the method can effectively increase the flutter velocity of the actuator-fin system.
引文
[1]陈桂彬,邹丛青,杨超.气动弹性设计基础[M].北京:北京航空航天大学出版社,2004.Chen Guibin,Zou Congqing,Yang Chao.Funda-mentals of aeroelastic design[M].Beijing:Press of Beijing University of Aeronautics and Astronautics,2004
[2]Won-Ho Shin,et al.Nonlinear aeroelastic analysis for a control fin with an actuator[J].Journal of Aircraft,2007,44(2):597-605.
[3]杨超,吴志刚.导弹气动伺服弹性稳定性分析[J].飞行力学,2000,18(4):1-5.Yang Chao,Wu Zhigang.Aeroservo-elastic stability of missile[J].Flight Dynamics,2000,18(4):1-5.
[4]Tiffang S H,Karpel M.Aeroservoelastic modeling and applications using minimum-state approximations of the unsteady aerodynamics[R].AIAAPaper 89-1188,1989.
[5]王文亮.结构振动与动态子结构方法[M].上海:复旦大学出版社,1985.Wang Wenliang.Vibration and dynamic substructure method[M].Shanghai:Fudan University Press,1985.
[2]Won-Ho Shin,et al.Nonlinear aeroelastic analysis for a control fin with an actuator[J].Journal of Aircraft,2007,44(2):597-605.
[3]杨超,吴志刚.导弹气动伺服弹性稳定性分析[J].飞行力学,2000,18(4):1-5.Yang Chao,Wu Zhigang.Aeroservo-elastic stability of missile[J].Flight Dynamics,2000,18(4):1-5.
[4]Tiffang S H,Karpel M.Aeroservoelastic modeling and applications using minimum-state approximations of the unsteady aerodynamics[R].AIAAPaper 89-1188,1989.
[5]王文亮.结构振动与动态子结构方法[M].上海:复旦大学出版社,1985.Wang Wenliang.Vibration and dynamic substructure method[M].Shanghai:Fudan University Press,1985.