aeroelastic model is developed to analyze aeroelastic stability of helicopter rotor blade with swept tips.
通过建立具有后掠桨尖旋翼气弹稳定性的分析模型 ,研究后掠桨尖旋翼气弹的稳定性。
a refined aeroelastic model of a helicopter rotor blade with swept tips is established based on model matching.
以动力学模型和气动模型相匹配为原则,建立了后掠桨尖旋翼的细致气弹模型。
the coupled flap-lag flutter stability of a helicopter rotor blade in hover is investigated by using a finite element formulation based on the principle of minimum potential energy.
本文用基于最小位能原理的有限元方法研究了直升机悬停时旋翼浆叶挥舞—摆振耦合颤振。
a support beam for connecting a lift generating wing section of a helicopter rotor blade with a rotor hub, said support beam comprising.
支持梁连接电梯发电翼的第一个直升机旋翼叶片与转子枢纽的地位,表示支持梁,包括。
the aeroelastic analysis of a helicopter rotor blade with the controlled oscillating trailing edge flap is presented by building an aeroelastic model of the new concept rotor blade.
通过建立带受控振蕩附翼的新概念旋翼气动弹性分析模型,研究了采用受控振蕩附翼的直升机旋翼气动弹性特性及其在降低旋翼振动载荷方面的有效性。
surface pressure data from 3 d unsteady free wake panel method has been used to predict the helicopter rotor blade vortex (bvi) interaction noise.
由三维自由尾迹非定常板元方法计算的三元非定常气动力出发,计算直升机旋翼桨涡干扰噪声。