无周期变距旋翼气弹动力学研究

Rotorcraft can hover and plays an irreplaceable role, but its rotor motion and flight control are very complicated. The Applicant invented a new configuration of the cyclicless-pitch rotorcraft and has been granted the national patent. Comparing with the conventional rotorcraft, the cyclicless-pitch rotorcraft does not make the flapping, lagging and cyclic pitching motions of blade, and its hub structure, blade motion and flight control are simpler. However, the change of configuration of the cyclicless-pitch rotor may result in the change of aeroelastic dynamic model and aeroelastic dynamics of the rotor, and affecting the flight performance and safety of the cyclicless-pitch rotorcraft. Hence, it is very important to investigate the aeroelastic dynamics of the cyclicless-pitch rotor. In this project, according to the configuration features of the cyclicless-pitch rotor, the aeroelastic dynamic problems on aeroelastic dynamic modeling, dynamic properties, responses and stabilities of the cyclicless-pitch rotor are to be investigated deeply to establish the methods for the aeroelastic dynamic modeling and analysis of the cyclicless-pitch rotor, to reveal the formation mechanism, changing rules and influence factors of these aeroelastic dynamic problems of the cyclicless-pitch rotor, and to provide the basic theory and analytical methods for dynamic design of the cyclicless-pitch rotor, and also to provide the effective methods for solving the basic scientific problems on the aeroelastic dynamic modeling and analysis of complex rotating flexible structures.

旋翼飞行器能空中悬停而具有不可替代的作用，但旋翼飞行器的旋翼运动和飞行控制都很复杂。申请人发明了无周期变距旋翼飞行器新构型，授权了国家发明专利。与常规旋翼飞行器相比，无周期变距旋翼桨叶无需做挥舞、摆振和周期变距运动，桨毂结构、桨叶运动和飞行操纵都较简单。但是，无周期变距旋翼构型的变化，会导致旋翼气弹动力学模型和气弹动力学问题发生变化，影响到无周期变距旋翼飞行器的飞行性能和飞行安全。因此，研究无周期变距旋翼气弹动力学十分重要。本项目针对无周期变距旋翼的构型特点，开展无周期变距旋翼气弹动力学建模、气弹动特性、动响应和动稳定性等气弹动力学问题的深入研究，建立无周期变距旋翼气弹动力学建模与分析方法，揭示无周期变距旋翼气弹动力学问题的形成机理、变化规律和影响因素，为无周期变距旋翼的动力学设计提供基础理论和分析方法，也为解决复杂旋转柔性结构的气弹动力学建模与分析等基础科学问题提供有效的方法。

本项目研究了无周期变距旋翼气弹动力学建模、气弹动特性、动响应和动稳定性，开展了无周期变距旋翼模型研制及地面试验，建立了无周期变距旋翼气弹动力学模型及气弹动特性、动响应和动稳定性分析方法，揭示了无周期变距旋翼气弹动特性、动响应和动稳定性的形成机理、变化规律和影响因素。在完成了本项目研究基础上，以旋翼动力学为主线，开展了复合材料旋翼桨叶大变形气弹动力学、无轴承复合材料旋翼/机体耦合系统气弹动力学、倾转旋翼/机体耦合系统气弹动力学、旋翼气弹激振力引起的机体振动主动控制等四方面的拓展研究，建立了相关旋翼及旋翼/机体耦合系统的气弹动力学模型、气弹响应、气弹稳定性分析方法以及旋翼气弹激振力引起的机体振动主动控制新方法。本项目研究为无周期变距旋翼气弹动力学设计及相关的旋翼及旋翼/机体耦合系统气弹动力学设计提供了理论基础和分析方法。

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