【摘要】：空間碎片對在軌航天器安全的威脅越來越大,為了提高航天器對毫米級空間碎片的抗撞擊能力,進行必要的風險評估,需要在地面進行一系列的超高速撞擊模擬實驗。而航天器實際運行環(huán)境極為復雜,包括空間碎片環(huán)境、空間熱環(huán)境、電子輻照環(huán)境等,這些極大影響了航天器的壽命及可靠性。本文以空間碎片防護為背景,借助高速撞擊地面模擬設備,研究極端溫度環(huán)境和熱循環(huán)環(huán)境等空間熱環(huán)境對航天器填充式防護結構防護性能的影響,以期發(fā)現(xiàn)溫度效應對玄武巖和Kevlar等編織物防護材料抵抗非金屬彈丸高速沖擊能力的影響,為航天器防護結構設計提供一定的參考依據(jù)。首先,通過二級輕氣炮地面撞擊實驗研究了玄武巖纖維和Kevlar纖維兩種不同編織材料填充式防護結構在不同非金屬彈丸以一定速度撞擊下的損傷特性,以及填充層在溫度交變處理前后對防護結構防護性能的影響規(guī)律和彈丸在溫度交變處理前后對其撞擊特性的影響規(guī)律。其中,溫度交變處理溫度變化范圍為203K~423K。其次,研究玄武巖纖維和Kevlar纖維兩種填充式防護結構在極端溫度環(huán)境下的撞擊特性,以及溫度對其防護性能的影響規(guī)律。實驗溫度設定分別為低溫(210K)、常溫(293K)和高溫(420K)。每一組溫度對比實驗均在相近溫度下進行。最后,研究了空間熱環(huán)境混合損傷效應對不同非金屬彈丸撞擊填充式防護結構防護性能的影響,包括彈丸和填充材料混合溫度交變處理實驗和極端溫度情況下混合溫度交變處理實驗。并總結本次研究所得出的具有實際工程意義的主要結論,指出了本文存在的不足和進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.
【學位授予單位】：哈爾濱工業(yè)大學
【學位級別】：碩士
【學位授予年份】：2016
【分類號】：V528
，

本文編號：2126407