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针对典型超音速舵面,采用基于CFD(computational fluid dynamic)技术的当地流活塞理论计算气动载荷,运用等效线化方法分析带有间隙非线性的舵面颤振特性。研究飞行迎角和舵面间隙大小对系统极限环颤振特性的影响规律。计算结果表明,适当赋予一定的气动预载荷、减小间隙大小等措施,可以提高带有间隙舵面的气动弹性稳定性。对于该舵面模型而言,无间隙颤振速度和舵面间隙大小满足国军标要求时,有间隙舵面在实际飞行中不会发生破坏性颤振,只在0°迎角情况下才会出现微幅极限环运动。
For a typical supersonic rudder surface, a local flow piston theory based on the CFD (computational fluid dynamic) technique is used to calculate the aerodynamic loads and the equivalent linearization method is used to analyze the flutter characteristics of the rudder surface with a gap nonlinearity. The influences of the flight angle of attack and rudder clearance on the characteristics of the system limit cycle flutter are studied. The calculation results show that aeroelastic stability with a clearance rudder surface can be improved by properly giving certain aerodynamic preload and reducing the clearance size. For the rudder model, the clearance-free flutter velocity and the size of the rudder clearance satisfy the requirements of the national military, the clearance rudder in the actual flight will not occur destructive flutter, only in the case of 0 ° angle of attack There will be a slight limit ring movement.