摘要
以正常式布局空空导弹折叠舵为研究对象,开展给定飞行条件下折叠舵展开过程气动载荷风洞试验,给出了折叠舵展开过程中的气动载荷,分析了气动载荷对折叠舵展开过程的影响,并对折叠舵受载情况进行了相应的CFD仿真,从理论上解释了折叠舵受载的合理性。结果表明,在给定飞行条件下,气动载荷有助于迎风折叠舵展开;跨音速时气动载荷阻碍背风折叠舵展开,超音速时气动载荷先利于再阻碍背风折叠舵展开。
Wind tunnel tests were conducted on an air-to-air missile with folded tails under specific flight conditions, and the aerodynamic loads during the deployment process were given. The effects of the aerodynamic loads on the deployment process were analyzed, and CFD calculations were performed to explore the mechanism. Results demonstrate that aerodynamic loads accelerate the deployment process for tails on the windward side under given flight conditions, but decelerate the process for tails on the leeward side in transonic regime, and first accelerate then decelerate the process in supersonic regime.
出处
《弹箭与制导学报》
CSCD
北大核心
2014年第3期154-156,178,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
折叠舵
空空导弹
气动载荷
风洞试验
计算流体力学
folded tail
air-to-air missile
aerodynamic load
wind tunnel test
computational fluid dynamics
