微小型电动垂直起降无人机总体设计方法及特殊参数影响  

Preliminary design method for miniature electric-powered vertical take-off and landing unmanned airial vehicle and effects of special parameters

作　　者：唐伟[1] 宋笔锋[1] 曹煜 杨文青[1] TANG Wei SONG Bifeng CAO Yu YANG Wenqing(School of Aeronautics, Northwestern Polytechnical University, Xi＇an 710072, China)

机构地区：[1]西北工业大学航空学院,西安710072

出　　处：《航空学报》2017年第10期115-128,共14页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(11402208)~~

摘　　要：针对微小型电动垂直起降无人机(VTOL mEUAV),分析其设计难点,通过理论分析提出了一种基于特殊参数的总体设计方法,并基于算例进行了特殊参数的计算和影响分析。从翼载荷的选择、起飞总重迭代估计、无人机的平衡与操纵分析和飞翼布局设计方面详细阐述总体设计方法的过程,并针对特殊设计的一套动力系统X型飞翼尾坐式垂直起降无人机,进行功重比、动力系统工作点特性匹配及动力系统安装角等特殊参数的选择和影响分析,最终基于设计结果进行原理样机制作与飞行试验,证明了设计方法的有效性。研究结果表明,不同设计目标会引起翼载荷的选择和功重比的变化,螺旋桨与电机的匹配特性极大地影响动力系统效率与能源选择,合理选择动力系统的安装角与偏转方向可在基本不影响整体性能的情况下有效地改善操纵特性。The difficulties of the design of the miniature Electric-powered Vertical Take-Off and Landing Unmanned Aerial Vehicle （VTOL mEUAV） are analyzed,and a preliminary design method based on special parameters is proposed according to theoretical analysis. The choice of wing-load, estimation of total weight, the analysis of balance and control, and the design of tailless wing are described. The special parameters concerning power-to-weight ratio, propulsion matching and mounted in- cidence of a X-type tailless tail-sitter VTOL UAV equipped with one set of propulsion are then selected and analyzed. Based on the design results,the manufactory and flight tests are used to verify the design method. The results show that different de- sign objective leads to different wing-load and power-to-weight ratio; propulsion efficiency and energy is greatly affected by motor and propeller matching; the suitable incidence of proplusion and deflected direction can improve the yaw control in hov- er without decreasing the whole property.

关 键 词：垂直起降无人机 总体设计方法 X型飞翼 功重比 动力系统匹配工作点 安装角 偏航操纵改善 

分 类 号：V221[航空宇航科学与技术—飞行器设计]