This dissertation proposes a flapping control mechanism to solve the flight power problems in hovering flight control of the insect-like flapping micro aerial vehicles(IFMAVs).
仿真结果验证了此操控机制可以较好地解决仅一对翼的仿昆扑翼飞行器飞行动力问题。
The influences of nonuniform vertical flow on helicopter trim controls and regressive lag modal damping levels were analyzed in hovering and forward flight.
分析了直升机从悬停到小速度前飞时，定常垂直气流的非均匀分布对直升机平衡操纵以及对系统摆振后退型模态阻尼的影响。
The influences of nonuniform vertical flow on helicopter trim controls and regressive lag modal damping levels were analyzed in hovering and forward flight.
分析了直升机从悬停到小速度前飞时，定常垂直气流的非均匀分布对直升机平衡操纵以及对系统摆振后退型模态阻尼的影响。
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