Dynamic stability and control laws of a hingeless rotor helicopter were studied.

研究了无铰直升机动稳定性、操纵性和控制问题。

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The experimental results verify that the feasible theory can be used to investigate the effects of structural parameters of hingeless rotor on aeroelastic stability.

试验证明该理论可行并能用于研究无铰旋翼结构参数对桨叶气弹稳定性的影响，也能用于直升机旋翼的型号设计。

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The experimental results verify that the feasible theory can be used to investigate the effects of structural parameters of hingeless rotor on aeroelastic stability.

试验证明该理论可行并能用于研究无铰旋翼结构参数对桨叶气弹稳定性的影响，也能用于直升机旋翼的型号设计。

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