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针对无人直升机旋翼桨叶性能改进升级的实际需求,以200 kg级无人机旋翼为原型建模,利用COMOSOL软件对直升机桨叶特性进行仿真分析研究。基于叶素法建立了桨叶升力的数学模型,克服了常规旋翼动力学仿真分析时气动载荷加载棘手的难题;通过研究直升机桨叶的空间旋转运动与其弹性变形间的耦合关系,得出了桨叶攻角、升力、桨尖位移随总距以及周期变距的变化曲线。将仿真结果与常规数值分析结果比较,验证了仿真结果的准确性。根据仿真结果提出了对桨叶迎角、桨叶前缘刚度等的具体改进建议,可为桨叶的改进设计提供参考依据。
According to the actual demand of performance improvement and upgrade of unmanned helicopter rotor blades, a prototype of 200 kg UAV rotor was modeled, and the propeller characteristics of helicopter were simulated by COMOSOL software. The mathematical model of blade lift is established based on the method of blade, which overcomes the difficult problem of aerodynamic load loading in conventional rotor dynamics simulation analysis. By studying the coupling relationship between helicopter blade’s spatial rotation and its elastic deformation, Angle, lift, tip displacement with the total distance and the cycle of the pitch curve. The simulation results are compared with the conventional numerical analysis to verify the accuracy of the simulation results. Based on the simulation results, some specific suggestions for improving the blade angle of attack and blade leading edge stiffness are proposed, which can provide reference for the improved design of the blade.