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首先建立了带襟翼翼型的非定常气动力模型,继而基于Peters-He广义动态尾迹理论,考虑襟翼偏转对电控旋翼叶素环境的影响,建立了电控旋翼有限状态尾迹模型;进一步基于Theodorsen理论推导出电控旋翼桨叶挥舞响应与桨叶变距和襟翼操纵量的关系,综合以上建立了电控旋翼气动特性分析模型.以改进型电控旋翼试验系统为平台进行了风洞试验,测量了不同风速、不同襟翼操纵条件下的电控旋翼气动力、桨距、襟翼偏角及旋翼挥舞角的变化情况.理论计算结果与试验数据符合情况良好,验证了所建立的分析模型的正确性,并得出以下结论:旋翼转速一定时,桨叶变距与襟翼操纵基本呈线性关系;旋翼拉力随襟翼总距的增加而逐渐减小,襟翼总距较大时,其实际气动效率略有下降;前飞状态时,襟翼总距操纵会引起桨叶的纵向周期变距.
Firstly, the unsteady aerodynamic model with flap airfoil is established, and then based on the Peters-He generalized dynamic wake theory, the finite state tail rotor model of the electronically controlled rotor is established considering the influence of flap deflection on the electrically controlled rotor blade vane environment. Theodorsen theory deduces the relationship between the waving response of the electronically controlled rotor blade and the blade pitch and the flap manipulation amount, and based on the above, establishes the aerodynamic characteristics analysis model of the electronically controlled rotor.With the improved electronically controlled rotor test system as the platform, The changes of the aerodynamic force, the pitch, the deflection angle of the flap and the swing angle of the rotor under different wind speeds and different flap manipulation conditions were measured.The results of the theoretical calculation are in good agreement with the experimental data, and the results show that the established The correctness of the model is analyzed and the following conclusions are drawn: when rotor speed is constant, blade pitch is basically linear with flap handling; rotor tension decreases with the increase of flap total distance, , The actual aerodynamic efficiency decreases slightly; during the pre-flight condition, the flap pitch control will cause the blade to change its longitudinal periodicity.