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硬质落球大气探测技术
引用本文:韩连刚,杨明星,齐鑫,王珂,桂苏嘉.硬质落球大气探测技术[J].空间科学学报,2019,39(5):655-661.
作者姓名:韩连刚  杨明星  齐鑫  王珂  桂苏嘉
作者单位:西安航天动力技术研究所固体火箭发动机燃烧、热结构与内流场国防科技重点实验室 西安710025;西安航天动力技术研究所固体火箭发动机燃烧、热结构与内流场国防科技重点实验室 西安710025;西安航天动力技术研究所固体火箭发动机燃烧、热结构与内流场国防科技重点实验室 西安710025;西安航天动力技术研究所固体火箭发动机燃烧、热结构与内流场国防科技重点实验室 西安710025;西安航天动力技术研究所固体火箭发动机燃烧、热结构与内流场国防科技重点实验室 西安710025
摘    要:为拓展大气探测高度范围,开展了硬质落球大气探测技术研究.以7inch硬质落球为例,开展了弹道仿真计算,进一步利用参考大气数据推算了落球可能承受的气动阻力加速度,显现出对加速度测量准确性的高要求;分析了杆臂效应引入的附加加速度及其对加速度测量结果的干扰程度;讨论了几种典型的阻力系数计算方法及其计算偏差状况;考虑了可能的电磁兼容风险及小型化设计与制造的必要性.基于落球工作机理与上述关键技术、特性的分析与研究,完成了一种硬质落球设计,确定了运动参数的测量方法、杆臂效应的抑制措施,明确了落球总体性能指标.通过演示验证飞行试验实测数据与仿真数据的对比分析,证明了技术方案的可行性、合理性、实际测量结果与预期的符合性. 

关 键 词:硬质落球  主动落球  大气探测
收稿时间:2018-07-05

Rigid Falling Sphere Technics in Air Observation
Institution:National Defense Science and Technology Key Laboratory of Solid Rocket Motor Combustion, Internal Flow and Thermo-Structure, Institute of Xi'an Aerospace Solid Propulsion Technology, Xi'an 710025
Abstract:In order to increase the height range of air observation, the rigid falling sphere technics is researched. Taking a 7-inch rigid falling sphere for instance, the trajectory simulation has been done. Along with the reference atmospheric data, the quantity of the acceleration that the sphere should bear is reckoned, showing the strict requirement for the acceleration measurement accuracy. The amount of interference of accessional portion of acceleration caused by lever arm effect is analyzed. Some drag calculation method and error are discussed and compared. The risk of EMC and the needs of miniaturized design are also considered. With the working principle of the rigid falling sphere and the analysis of its key technical features mentioned above, a type of rigid falling sphere design has been done, including the kinetic parameter measuring, the lever arm effect restraining, and the overall index design. One of the three rigid falling sphere manufactured and tested was launched, almost all of measuring data along the trajectory was obtained. Through the comparative analysis between the really measuring data acquired during the demonstration flight test and that resulted from the simulation, the technical proposal has been proved to be feasible and rational, and a clear path for further research is established. 
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