空间凸轮-螺旋组合式折叠翼面展开机构设计及其运动特性分析  

Design and Kinematic Characteristics Analysis on Space Cam-helix Deployable Mechanism of Folding Missile Wing

作　　者：胡明[1] 黎德蓓[1] 陈文华[1] 张苗苗[1] 钱萍[1] 

机构地区：[1]浙江理工大学机电产品可靠性技术研究浙江省重点实验室,杭州310018

出　　处：《中国机械工程》2012年第12期1475-1478,共4页China Mechanical Engineering

基　　金：国家自然科学基金资助项目(51006134;50935002);浙江省重点科技创新团队项目(2010R50005);2010;2011年度浙江省省级公益性技术应用研究计划资助项目(2011C31G2060082;2011C31076);浙江省自然科学基金资助项目(Y1100777)

摘　　要：提出新型空间凸轮—螺旋组合式折叠翼面展开机构,分析其工作原理,确定其相关技术参数。基于解析法与反转法,对折叠翼面展开机构的功能执行部件———空间圆柱凸轮机构进行了运动规律设计和包括凸轮槽道廓线、压力角及廓线曲率半径的设计,建立了折叠翼面展开机构展开运动学理论模型并进行了求解,结果证明折叠翼面展开机构符合设计要求,其运动规律设计正确。A new kind of space cam--helix deployable mechanism of missile folding wing was pro- vided herein, and then its working principles and technical parameters were determined. Based on ana- lytical method and reversal theory,its motion law,cam profile curve,its pressure angle and radius of profile curve on the space cam mechanism of folding wings were designed. Theoretical modeling of deploying kinematics were made and solved. Results show that the deployable mechanism of missile fold- ing wing meets the design requirements and its motion law design of the folding wing is correct.

关 键 词：折叠翼面展开机构 圆柱移动凸轮机构 螺旋传动机构 凸轮廓线 展开运动 

分 类 号：V223.4[航空宇航科学与技术—飞行器设计]