摘要
新型旋翼气囊复合动力无人飞行器主要原理是借助四旋翼与空气静升力提供升力;在该无人机总体设计方案的基础上,对应用变距旋翼技术进行前飞驱动时的气动性能展开分析研究。对变距旋翼模型采用标准κ-ε湍流模型、RNG模式和主导漩涡流模式;并通过数值模拟研究不同转速、桨距角在前飞状态下的气动特性。同时在地面风洞试验台对在前飞状态下模型旋翼进行了试验研究;并且试验结果与计算结果基本吻合。得出该无人机在巡航状态下,螺旋桨转速在4 000 r/min,桨距角14°具有最佳的螺旋桨效率。为新型旋翼气囊无人飞行器的整体优化以及工程应用提供了参考依据。
The Unmanned Aerial Vehicle （UAV） main principle is with the help of four rotor to provide lift and aerostatie lift. Based on the overall design scheme, variable pitch rotor as driving the aerodynamic performance is in which the standard k-s, RNG model and Swirl dominated flow model is used. Experimental research is carried out ont the helicopter model rotor on Forwarding Flight in the Ground wind tunel test, and the calculation results agree well with experimental results. The UAV in cruise mode, speed in 4 000 r/rain, pitch angle 14° has the best efficien- cy of propeller. Reference is orovided for new rotor airbag vehicle overall optimization and engineering application.
出处
《科学技术与工程》
北大核心
2014年第31期113-118,共6页
Science Technology and Engineering
基金
航空基金(BA201106150)资助
关键词
无人机
变距旋翼
气动性能
unmannde aerial veicle variable pitch of rotor aerodynamic performance
