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提出一种桨叶结构、气动和惯性耦合的旋翼系统综合分析方法 ,将桨叶绕挥舞、摆振及变距铰的刚性转角作为广义坐标 ,计入了桨叶整体运动和自身中等弹性变形之间的动力学耦合效应 ,桨叶弹性变量通过有限元法进行离散 ,翼型剖面气动力采用 Leishman-Beddoes二维非定常和动态失速模型 ,由自由尾迹模型得出桨盘的非均匀入流 ,依据柔性多体系统动力学方法推导出桨叶前飞状态下的非线性周期时变动力学方程。对 Newmark隐式数值积分方法进行改进 ,用于求解旋翼桨叶的响应。以法国 SA3 49/2小羚羊直升机的试飞测试数据为依据 ,验证了方法的有效性。
A comprehensive analysis method of rotor system with blade structure, aerodynamic and inertial coupling was proposed. The rigid corner of the blade about waving, shimmy and pitch change was defined as a generalized coordinate, which included the whole movement of the blade and its own medium elastic deformation The dynamic coupling effect between blades and the blade elastic variables are discretized by the finite element method. The aerodynamic profile of the aerofoils is Leishman-Beddoes two-dimensional unsteady and dynamic stall model. The non-uniform inflow of propeller disks is obtained from the free wake model. The flexible multi-body system dynamics method is used to derive the nonlinear periodic dynamic mechanical equations of the blade before flight. The Newmark implicit numerical integration method is improved to solve the rotor blade response. Based on the flight test data of the French SA3 49/2 Steenbok helicopter, the method is validated.