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基于跨声速非定常气动力求解的重叠场源法,开展了弹性飞机跨声速机动载荷计算方法研究,为现代飞机结构强度设计提供更加可靠和精确的临界载荷计算方法。首先通过采用重叠场源法求解关于62%根弦俯仰振荡的LANN机翼在马赫数为0.822的非定常气动力并与实验结果进行对比,验证了重叠场源法对跨声速激波效应预测和非定常气动力计算的能力;其次应用频域气动力有理近似技术拟合场源法计算得到的广义气动力系数矩阵,建立了机动载荷分析的状态空间模型;然后完成了某型民用飞机俯仰机动载荷分析,研究了俯仰机动飞行情况下飞机机体状态量及飞机部件载荷响应规律。计算结果表明:考虑机体弹性变形后,机翼和平尾气动载荷响应最大值分别减小了5.1%和10.6%,升降舵气动载荷响应最大值增大了16.2%,在飞机结构强度设计中必须考虑机体弹性效应对飞机部件载荷的影响。
Based on the overlapped field source method for transonic unsteady aerodynamic solutions, a study on transonic acoustic maneuvering load calculation is carried out to provide a more reliable and accurate critical load calculation method for modern aircraft structural strength design. First, the unsteady aerodynamics of the LANN wing with 62% root-pitch pitching oscillation is solved by using the overlapped field source method and compared with the experimental results. It is verified that the overlapping field source method can predict the transonic shock effect and Secondly, the generalized aerodynamic coefficient matrix calculated by the field source method is fitted by the rational approximation of the aerodynamic force in the frequency domain, and the state space model of the maneuvering load analysis is established. Then, a civil aircraft pitch maneuver The load analysis is carried out to study the state quantity of aircraft body and the response of aircraft components under the maneuver of pitch maneuver. The calculation results show that the maximum value of the dynamic response of the tail wing and the tail tail decreases by 5.1% and 10.6%, respectively, and the maximum value of the aerodynamic load response of the elevator increases by 16.2% after taking into account the elastic deformation of the wing. The structural design of the aircraft structure Effect of Elasticity on Aircraft Component Loads.