无人直升机变距尾桨的仿真模型验证

Numerical Simulation Model Verification of Variable Pitch Tail Rotor on UAV

本文以一架无人直升机的电动变距尾桨为基础,建立关于尾桨升力计算的仿真模型,并对特定工况下采用不同湍流模型的计算结果进行对比分析;在此基础上,选择最佳的湍流模型进行不同桨距下尾桨的数值模拟,得到尾桨升力随桨距变化的曲线;最后将升力曲线与试验数据作对比,验证尾桨仿真模型的可靠性。

This paper builds a numerical simulation model of variable pitch electric tail rotor for lift calculation, based on a specific UAV, and the compared analysis of the numerical simulation consequences under different turbulence model are performed. Afterwards, the best turbulence model was chosen to run numerical simulations under different pitch and obtain the data of lift value varying with pitch. At last, the comparison between calculation value and experiment value determines the reliability of the numerical simulation model.