摘要
以某战术导弹折叠尾翼为研究对象,采用动态测力天平和加速度传感器以及角度传感器作为测量元件,获得了折叠尾翼在快速展开过程中气动力的试验结果。还介绍了尾翼展开过程中气动力的处理方法,不同试验状态下对数据的特殊处理。对试验结果进行分析后表明,所采用的试验技术可行,试验数据可靠。
The purpose of this paper is to investigate the dynamic force measurement test of folded wing deploying by using the measurement components of dynamic test balance and acceleration sensor and angle sensor. Also the paper introduces the methods about the aerodynamic force calculation and the special processing ways in different test states. The results indicate that the tests are reliable.
出处
《实验流体力学》
CAS
CSCD
北大核心
2007年第2期46-49,62,共5页
Journal of Experiments in Fluid Mechanics
关键词
战术导弹
折叠尾翼
动态测力
风洞试验
tactical missiles
folded wing
dynamic force measurement
wind tunnel test
