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基于Theodorsen非定常气动力理论,以大展弦比均匀直机翼为研究对象,建立了系统的气动弹性响应方程。选取二阶弯曲和二阶扭转模态,采用V-g法求解了系统的颤振速度。基于Kussner函数,建立了锐边突风系统模型,并推导了在弯曲和扭转模态阶数为Nw和Nα下的系统状态方程,仿真研究了加入突风后系统的气动弹性响应。结果表明,加入突风后翼尖响应振幅增大。
Based on the Theodorsen unsteady aerodynamic theory, the aeroelastic response equation of the system is established with a large aspect ratio uniform wing as the research object. The second-order bending and the second-order torsional modes were selected, and the flutter velocity of the system was solved by V-g method. Based on the Kussner function, a sharp-edged gusting system model is established and the state equation of the system under the bending and torsional modal orders Nw and Nα is derived. The aeroelastic response of the system after the gust addition is simulated. The results show that the amplitude of wing tip response increases with the addition of gusts.