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无减摆器旋翼具有桨毂结构简单、桨毂气动阻力小、桨毂维护简便等优点,但取消了桨毂减摆器后必须确保桨叶在摆振方向有足够的阻尼以保证桨叶的摆振稳定性。基于气弹耦合的方法是实现无减摆器旋翼桨叶摆振稳定性的一个有效方法。建立了无减摆器无铰式旋翼桨叶带有预锥角、下垂角、后掠角和预扭角等结构参数的非线性气弹动力学模型,利用伽辽金方法把桨叶偏微分运动方程简化为非线性常微分平衡方程和关于平衡位置的小扰动运动方程,分析了桨叶的气弹稳定性并进行了参数影响分析。数值结果表明,合理的桨叶结构参数和气弹耦合可确保无减摆器旋翼桨叶在摆振方向的气弹稳定性。
No sway rotor rotor with a hub structure is simple, small aerodynamic resistance of the hub, the hub is easy to maintain and so on, but canceled hub hedgehog must ensure that the blade has sufficient damping in the shimmy direction to ensure that the blade Shimmy stability. The method based on the aeroelastic coupling is an effective method to realize the rotorless rotor blade shimmy stability. A non-linear aerodynamic model of a non-hinged rotor blade with pre-cone angle, sag angle, sweep angle and pre-torsion angle is established. By using the Galerkin method, The equations of motion are simplified to the nonlinear ordinary differential equations and the perturbed equations of motion for equilibrium positions. The aeroelastic stability of the blades is analyzed and the parameter influence analysis is carried out. The numerical results show that the reasonable blade structure parameters and the gas-air coupling can ensure the aeroelastic stability of the rotor blades without hesitation in the shimmy direction.