空间热环境下非金属弹撞击填充式防护结构损伤特性研究

发布时间：2018-07-16 12:34

【摘要】：空间碎片对在轨航天器安全的威胁越来越大,为了提高航天器对毫米级空间碎片的抗撞击能力,进行必要的风险评估,需要在地面进行一系列的超高速撞击模拟实验。而航天器实际运行环境极为复杂,包括空间碎片环境、空间热环境、电子辐照环境等,这些极大影响了航天器的寿命及可靠性。本文以空间碎片防护为背景,借助高速撞击地面模拟设备,研究极端温度环境和热循环环境等空间热环境对航天器填充式防护结构防护性能的影响,以期发现温度效应对玄武岩和Kevlar等编织物防护材料抵抗非金属弹丸高速冲击能力的影响,为航天器防护结构设计提供一定的参考依据。首先,通过二级轻气炮地面撞击实验研究了玄武岩纤维和Kevlar纤维两种不同编织材料填充式防护结构在不同非金属弹丸以一定速度撞击下的损伤特性,以及填充层在温度交变处理前后对防护结构防护性能的影响规律和弹丸在温度交变处理前后对其撞击特性的影响规律。其中,温度交变处理温度变化范围为203K~423K。其次,研究玄武岩纤维和Kevlar纤维两种填充式防护结构在极端温度环境下的撞击特性,以及温度对其防护性能的影响规律。实验温度设定分别为低温(210K)、常温(293K)和高温(420K)。每一组温度对比实验均在相近温度下进行。最后,研究了空间热环境混合损伤效应对不同非金属弹丸撞击填充式防护结构防护性能的影响,包括弹丸和填充材料混合温度交变处理实验和极端温度情况下混合温度交变处理实验。并总结本次研究所得出的具有实际工程意义的主要结论,指出了本文存在的不足和进一步深入研究的方向。
[Abstract]:Space debris is becoming more and more dangerous to the safety of orbit spacecraft. In order to improve the anti-collision ability of spacecraft to millimeter space debris and to carry out the necessary risk assessment, a series of super high-speed impact simulation experiments are needed on the ground, and the actual operating environment of the spacecraft is very complex, including space debris environment, space thermal environment, electricity. In this paper, the effects of space thermal environment on the protective energy of spacecraft filled protective structures are studied in this paper, with the background of space debris protection, and the impact of extreme temperature environment and thermal cycle environment on the protective energy of spaceship filled protective structures with the use of high speed impact ground simulation equipment. The protective material of Kevlar and other braiding resists the impact of the high speed impact of non metal projectiles. It provides some reference for the design of the spacecraft protection structure. First, two different woven materials filled with basalt fiber and Kevlar fiber are studied by the ground impact test of two stage light gas gun. The damage characteristics of the fixed velocity impact and the influence law of the filling layer on the protective structure of the protective structure before and after the temperature alternating treatment and the influence of the projectile on the impact characteristics before and after the temperature alternating treatment. The temperature change range is 203K~423K. next, and the two kinds of basalt fiber and Kevlar fiber are studied. The impact characteristics of the protective structure under extreme temperature and the influence of temperature on its protective performance. The experimental temperature is set at low temperature (210K), normal temperature (293K) and high temperature (420K). Each group of temperature comparison experiments are carried out at the same temperature. Finally, the mixed damage effect of space thermal environment is studied for different non metal projectiles. The impact of the protective structure of the impact filled protective structure, including the mixed temperature alternating treatment experiments on the mixing temperature of the projectiles and filling materials and the mixed temperature alternating treatment experiments under the extreme temperature condition, has been summarized, and the main conclusions of the actual engineering significance obtained by this study are summarized, and the shortcomings of this paper and the direction of further research are pointed out.
【学位授予单位】：哈尔滨工业大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V528
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本文编号：2126407