涡桨类无人机飞行试验参数计算分析研究  

Analysis and Calculation of Flight Test Parameters of a Turboprop UAV

作　　者：许军[1] Xu Jun(The 38th Research Institute of China Electronics Technology Group Corporation,Hefei 230088,Anhui,China)

机构地区：[1]中国电子科技集团公司第三十八研究所,安徽合肥230088

出　　处：《工程与试验》2023年第4期22-24,42,共4页Engineering and Test

摘　　要：针对一种涡桨类无人机飞行试验,计算分析无人机飞行试验相关气动参数。结合无人机飞行试验参数,建立无人机发动机推力计算方法,进行无人机推力特性计算分析、升力系数计算分析、阻力系数计算分析、升阻比计算分析等,并与风洞试验值进行对比分析。研究内容和方法可为无人机改进设计提供依据,并可为其他无人机飞行试验气动特性参数分析提供理论指导和工程借鉴。Aiming at the flight test of a turboprop UAV,the aerodynamic parameters related to the flight test of UAV are calculated and analyzed.Combined with the UAV flight test parameters,the thrust calculation method for UAV engine is established to carry out the thrust characteristics calculation and analysis,lift coefficient calculation and analysis,drag coefficient calculation and analysis,lift-drag ratio calculation and analysis,and the result are compared with the wind tunnel test values.The research contents and methods can provide reference for the improvement design of UAV,and provide theoretical guidance and engineering reference for aerodynamic characteristic parameter analysis of other UAV flight test.

关 键 词：无人机 涡桨发动机 升力系数 阻力系数 升阻比 

分 类 号：V217[航空宇航科学与技术—航空宇航推进理论与工程]