摘要
随着导弹技术的发展,导弹的种类越来越多,细长体导弹不断出现,对高速动导数试验也提出了相应特殊的要求。相比于常规布局导弹,细长体导弹高速动导数试验面临着角度天平无法在模型内腔安装、动态滚转力矩小导致测量精度低等技术问题。为实现细长体导弹滚转动导数测量,在FL-1风洞中建立了一套滚转动导数测量机构,相比于原始机构,进行了三方面改造:运动转换形式由"导轨"形式变为"内外环"形式、角度天平从模型内腔后移置尾支杆末端、测力天平采用特殊的结构形式设计。试验结果显示,同一模型、不同机构、不同期的重复性试验结果一致性较好,证明了试验机构的可靠性。目前,该装置已成功应用于某长细比达18的导弹型号试验任务,试验精度满足型号要求。
With the development of designing tech varieties, and slender missiles have been commonly desig the measurement of high-speed dynamic stability derivati conventional missile, slender missiles during dynamic difficulties such as no space for the installation of angul niques, missiles have ned. There are special more and more reqmrements on ves for slender missiles. In contrast to tests encounter much more technical ar balances inside test models and low measurement precision due to small magnitude of dynamic rolling moment. A new measurement rig for dynamic stability derivatives was developed to measure the rolling derivatives exerted on a slender missile in FL-1 wind tunnel. Compared with traditional rigs, the newly developed one achieves following improvements. First, the type of motion transform was changed leading track to inner and outer circle. Second, the angular balance was moved to the sting aft from inside the model. Third, the force-measuring balance was designed with special structures. The rolling derivatives were gained successfully exerted on the missile with a length-to-width ratio of 18. In order to validate the reliability of the new rig, some validation tests were conducted on a previous mode, which already has some test results from conventional rigs. The test results show that the measurements by different rigs have an excellent repeatability for direct damping derivative.
出处
《空气动力学学报》
CSCD
北大核心
2017年第2期214-219,共6页
Acta Aerodynamica Sinica
关键词
细长体导弹
滚转阻尼导数
精确测量
风洞试验
slender missile ~ roll damping derivative
accurate measurement
wind tunnel test
