折叠变体飞行器风洞试验模型设计与可靠性分析  

The Model Design and Reliability of one Morphing Aircraft with Folding Wing for Wind Tunnel Test

作　　者：李强[1] 李周复[1] 刘铁中[1] 

机构地区：[1]中国航空工业空气动力研究院,黑龙江哈尔滨150001

出　　处：《机械传动》2009年第6期82-85,共4页Journal of Mechanical Transmission

基　　金：总装备部预研基金(HK5703)

摘　　要：特种高速风洞试验模型设计一直是风洞试验领域的难点问题。针对某变体飞行器高速风洞试验任务提出的运动性能指标,设计开发了可控的折叠变体试验模型,对其设计方案及工作原理进行了阐述,并对传动机构进行了优化设计,而后对传动机构进行了可靠性分析与计算。结果表明该试验模型能够对机翼折叠变体角度进行连续、稳定和精确控制,完全达到了设计要求的各项指标。The special high-speed wind tunnel test model is a difficult problem in the aviation field. Aiming at the movement performance index of one morphing aircraft for high-speed wind tunnel,the controllable-folding morphing test model is designed. The design scheme and operating principle of the folding structure are represented,and optimum design and t reliability of the running mechanism are obtained. The analysis results indicated that the morphing angular of the folding test model could be continuous controlled accurately and stably. The test model meets design requirements.

关 键 词：变体飞行器 折叠 风洞模型 可靠性 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]