| 战术导弹折叠尾翼展开动态测力试验技术研究 |
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| 引用本文： | 贾毅,李甘牛.战术导弹折叠尾翼展开动态测力试验技术研究[J].实验流体力学,2007,21(2):46-49,62. |
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| 作者姓名： | 贾毅 李甘牛 |
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| 作者单位： | 南京航空航天大学航空宇航学院,南京,210016 |
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| 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.
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| 关 键 词： | 战术导弹 折叠尾翼 动态测力 风洞试验 |
| 文章编号： | 1672-9897（2007）02-0046-05 |
| 修稿时间： | 2006-04-212006-07-27 |
The dynamic test of folded wing deploying of some tactical missiles |
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| JIA Yi,LI Gan-niu.The dynamic test of folded wing deploying of some tactical missiles[J].Experiments and Measur in Fluid Mechanics,2007,21(2):46-49,62. |
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| Authors: | JIA Yi LI Gan-niu |
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| Institution: | Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China |
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| Abstract: | 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. |
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| Keywords: | tactical missiles folded wing dynamic force measurement wind tunnel test |
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