摘要
通过对柔性翼小型无人飞行器试验样机的研制试飞和相关气动分析与试验,研究了解决柔性翼小型无人飞行器的气动性能、飞行性能和操纵稳定性的思路和方法。试验样机试飞与相关风洞试验结果表明,可折叠柔性翼小型无人飞行器飞行稳定,操纵反应适当,具有广阔的应用前景。
From the flight test and relative aerodynamic analysis and test for the flexible wing miniature unmanned vehicle, the method on dealing with the aerodynamic feature, flight feature and operational stability has been researched. The flight test and relative wind tunnel test indicate that the flexible wing miniature unmanned vehicle flights steadily. The operating response of the vehicle is properly. The flexible wing miniature unmanned vehicle will have a great applied future.
出处
《飞行力学》
CSCD
北大核心
2007年第3期71-74,78,共5页
Flight Dynamics
基金
航天科技集团公司科技创新项目
关键词
小型无人飞行器
柔性翼
试验样机
风洞试验
试飞
miniature unmanned vehicle
flexible wing
prototype
wind tunnel test
flight test