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在建立倾转旋翼机飞机模式和直升机模式下的旋翼/短舱/机翼系统耦合气弹动力学分析模型的基础上,分析了倾转旋翼、机翼动力学参数对倾转旋翼机气弹稳定性的影响,得到了不同动力学参数对前飞时回转颤振速度和悬停时模态阻尼的影响曲线,对于倾转旋翼机动力学设计具有理论指导意义。
Based on the rotor-nacelle / wing system coupled aeroelastic dynamics model of tiltrotor aircraft and helicopter mode, the influences of tilting rotor and wing dynamics parameters on tilting rotor aeroelastic The influence of different dynamic parameters on the gyroscopic flutter velocities and the modal damping during hovering is obtained. It is of theoretical significance for the dynamic design of tilting rotorcraft.