一种无人直升机旋翼桨叶设计与动力学试验  

Rotor Blade Design and Dynamic Test of an Unmanned Helicopter

作　　者：刘帅 LIU Shuai(Suzhou Eavision Robotic Technologies Co.,Ltd.,Suzhou 215000)

机构地区：[1]苏州极目机器人科技有限公司,苏州215000

出　　处：《航空精密制造技术》2020年第6期30-33,37,共5页Aviation Precision Manufacturing Technology

摘　　要：本文系统的阐述了无人直升机旋翼桨叶的设计思路,基于某型单旋翼无人直升机的总体参数,首先对旋翼桨叶进行结构设计,然后分析和计算该桨叶剖面刚度。其次对桨叶的气动仿真计算,结合发动机特性评估桨叶悬停效率及悬停需用功率以及发动机可用功率等特性,再次应用动力学分析软件,分析旋翼桨叶的动特性,并与旋翼桨叶的动特性试验结合,验证的仿真数据与方法的正确性,最后采用CAMRADII软件,对旋翼桨叶进行动力学校核。从分析数据来看,该旋翼桨叶满足该无人直升机飞行要求。Based on the overall parameters of a single rotor unmanned helicopter, the rotor blade structure is designed. The blade section stiffness is analyzed and calculated. The aerodynamic simulation of the rotor blade is carried out. The hovering efficiency and power required for hovering and the available power of the engine are evaluated based on the characteristics of the engine. The dynamic characteristics of the rotor blade are analyzed by using the dynamic analysis software, and the correctness of the simulation data and method is verified by combining with the dynamic characteristics test of the rotor blade. By using the software Camrad II, the rotor blade is checked by dynamics. According to the analysis data, the rotor blade meets the flight requirements of the unmanned helicopter for the reference of relevant workers.

关 键 词：无人直升机 桨叶结构设计 气动分析 动力学分析 动力学试验 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程]