微小空间碎片撞击效应研究
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摘要
微小空间碎片作为一种空间环境要素,其数量巨大,航天器在轨道运行期间将不可避免的与之发生超高速碰撞,从而对航天器的寿命和可靠性形成威胁。国外从阿波罗登月计划开始研究微流星对航天器的威胁开始,一直关注微流星与微小空间碎片对航天器的威胁,通过天基探测、地面模拟实验等手段开展了大量研究,为航天器的安全设计和风险评估提供了重要的参数。国内,对微小空间碎片的研究目前还比较少。但是,随着我国航天事业的发展,有必要对微小空间碎片进行系统的研究。论文工作是通过等离子体加速器完成的,利用该装置在国内首次实现了能够加速15km/s的超高速微粒的方法;通过地面模拟实验获得了微小碎片撞击太阳电池玻璃盖片的实验规律,建立了太阳电池表面损伤的评估方法,开展了微小空间碎片累计撞击太阳电池的地面模拟实验;首次对微小空间碎片与原子氧协同效应以及微小碎片撞击诱发放电现象进行了探索性研究。
论文工作是在等离子体驱动微小碎片加速器上开展的,在论文主要内容开展前等离子体加速器正处于调试阶段,作为国内首台此类设备,其调试难度和工作量均很大。通过优化等离子体加速器的参数,在国内首次实现了加速微小碎片到15km/s的实验技术和方法。在等离子体加速器的调试过程中,研制出了理论相对成熟的压电测速和激光测速手段。根据超高速撞击形成等离子体的特性,创新地提出和实现了采用平面传感器收集撞击等离子体在线测量超高速微粒速度的新方法。实验表明,该新型超高速微粒速度测量方法测量精度高、时间分辨率高,而且原理简单成本低廉,是一种极有发展前途的方法。
论文的主要工作是利用等离子体加速器开展微粒超高速撞击太阳电池玻璃盖片的单次撞击实验和建立太阳电池表面损伤评估方法,并通过微粒超高速撞击太阳电池的累计撞击实验验证了表面损伤评估方法。通过大量的单次撞击试验,独立获得了微粒超高速撞击太阳电池玻璃盖片的撞击损伤规律,并结合master2005空间碎片模式给出的空间碎片的在轨分布情况,自主建立了微小空间碎片对太阳电池表面损伤的评估方法,评估结果与国外相关结果相符合。利用该方法首次揭示了造成太阳电池表面损伤的主要是5到500微米区间的空间微小碎片。实验得到了微小碎片累计撞击引起的太阳电池功率变化,表明这种影响主要是表面撞击损伤导致的太阳光透射率变化引起的,实验还揭示了微小空间碎片对太阳电池功率的影响比较小。首次利用累计撞击实验结果对上述表面损伤评估方法进行了验证,表明二者吻合较好。
对空间微小碎片与原子氧的协同作用以及碎片撞击诱发放电现象进行了探索性研究。利用等离子体加速器和基于潘宁离子源的原子氧模拟器进行了实验,证实了原子氧与碎片存在协同作用。结果显示碎片撞击能加剧原子氧对Kaptom材料的侵蚀作用,特别是对镀有防护涂层的Kapton材料,在考虑其抗原子氧性能时,必须考虑碎片与原子氧的协同效应。通过模拟试验,首次观测到微米级超高速微粒撞击形成的等离子体诱发放电的现象。因此必须对以上两种效应进行深入研究,确定其形成机制及可能给航天器带来的危害和风险。
In the space environment space debris has a large amount of numbers that the aircraft will invetably impact with small space debris and those impacts will be a threat to the lifetime and reliability of the aircraft. From Apollo Project the foreign countries began to research the effect of small astronautics on aircraft. A lot of research were carried out through on orbit detection ground simulation experiments and so on, which provided usful information for the security desin and risk evaluation for aircraft. The research about small space debris inboard is small. As the development of space appliance we need to study small space debris. The work presented in this paper is carried out in the plasma accelerator. On that instrument the method for accelerating small particle to 15km/s was obtained. Through ground simulation experiments the damage laws about small particle impact solar cell cover glass is obtained and on those laws the evaluation method for surface damage of solar cell cover glass is founded. The experiment about cumulative impacts on solar cell was carried out. At last the combined effect of small space debris impact and atomic oxygen and small space debris impact induced discharge was presented.
This paper is about the study on small space debris effect on aircraft which carried out through the plasma accelerator. At the beginging of the study the plasma drag small particle accelector is under research which is very difficult as the first of this kind of accelector. On that instrument through experiments the method for accelerating small particle to 15km/s was obtained. During the research of the accelector the velocity measure of small hypervelocity particle is very important and the piezoelectricity method and laser method is developed and used in the accelector system other than that the brand new method based on hypervelocity impact plasma collection was developed. Experiment result indicates that this new method has high precision in velocity measurement, the single width is narrow and the cost is cheap so is a very good method.
The main work of this paper is about the hypervelocity impact experiment of small particle on solar cell cover glass and cumulative impact experiment of small particles on solar cell which carried out through the plasma drag small particle accelector. During the impact experiments on solar cell cover glass, through a lot experiment results the damage laws is acquired and the transmission rate on the damage area is measured. Using the damage equation and the Master2005 space debris model the method for evaluate the surface damage of solar cell is acquired. The caculated result through this method is fit for the result of similar calculation abroad. And through the calculation we found that particles with diameters between 5um and 500um make the main contribution to the surface damage. The power decline of the solar cell after the cumulative impact experiment is fit for with the calculation through the surface damage evaluation method. Although the result indicates that the transimission decay result from surface damge is the main reason of power decline. Further more the small space debris has little effect on solar cells.
At last the combined effect of small space debris impact and atomic oxygen and small space debris impact induced discharge was presented. Using plasma drag small particle accelector and PIG atomic oxygen instruments the experiment was carried out and the result inditacts that the combined effect is obvious and especially serious for Kapton material with defence coat,so it’s important to consider this combined effect. The first experiment about discharge induced through hypervelocity by particles with diameter in micron scale was carried out. So we should pay attention to those phenomena and to found out the essence of those phenomena and is effect to aircraft.
论文工作是在等离子体驱动微小碎片加速器上开展的,在论文主要内容开展前等离子体加速器正处于调试阶段,作为国内首台此类设备,其调试难度和工作量均很大。通过优化等离子体加速器的参数,在国内首次实现了加速微小碎片到15km/s的实验技术和方法。在等离子体加速器的调试过程中,研制出了理论相对成熟的压电测速和激光测速手段。根据超高速撞击形成等离子体的特性,创新地提出和实现了采用平面传感器收集撞击等离子体在线测量超高速微粒速度的新方法。实验表明,该新型超高速微粒速度测量方法测量精度高、时间分辨率高,而且原理简单成本低廉,是一种极有发展前途的方法。
论文的主要工作是利用等离子体加速器开展微粒超高速撞击太阳电池玻璃盖片的单次撞击实验和建立太阳电池表面损伤评估方法,并通过微粒超高速撞击太阳电池的累计撞击实验验证了表面损伤评估方法。通过大量的单次撞击试验,独立获得了微粒超高速撞击太阳电池玻璃盖片的撞击损伤规律,并结合master2005空间碎片模式给出的空间碎片的在轨分布情况,自主建立了微小空间碎片对太阳电池表面损伤的评估方法,评估结果与国外相关结果相符合。利用该方法首次揭示了造成太阳电池表面损伤的主要是5到500微米区间的空间微小碎片。实验得到了微小碎片累计撞击引起的太阳电池功率变化,表明这种影响主要是表面撞击损伤导致的太阳光透射率变化引起的,实验还揭示了微小空间碎片对太阳电池功率的影响比较小。首次利用累计撞击实验结果对上述表面损伤评估方法进行了验证,表明二者吻合较好。
对空间微小碎片与原子氧的协同作用以及碎片撞击诱发放电现象进行了探索性研究。利用等离子体加速器和基于潘宁离子源的原子氧模拟器进行了实验,证实了原子氧与碎片存在协同作用。结果显示碎片撞击能加剧原子氧对Kaptom材料的侵蚀作用,特别是对镀有防护涂层的Kapton材料,在考虑其抗原子氧性能时,必须考虑碎片与原子氧的协同效应。通过模拟试验,首次观测到微米级超高速微粒撞击形成的等离子体诱发放电的现象。因此必须对以上两种效应进行深入研究,确定其形成机制及可能给航天器带来的危害和风险。
In the space environment space debris has a large amount of numbers that the aircraft will invetably impact with small space debris and those impacts will be a threat to the lifetime and reliability of the aircraft. From Apollo Project the foreign countries began to research the effect of small astronautics on aircraft. A lot of research were carried out through on orbit detection ground simulation experiments and so on, which provided usful information for the security desin and risk evaluation for aircraft. The research about small space debris inboard is small. As the development of space appliance we need to study small space debris. The work presented in this paper is carried out in the plasma accelerator. On that instrument the method for accelerating small particle to 15km/s was obtained. Through ground simulation experiments the damage laws about small particle impact solar cell cover glass is obtained and on those laws the evaluation method for surface damage of solar cell cover glass is founded. The experiment about cumulative impacts on solar cell was carried out. At last the combined effect of small space debris impact and atomic oxygen and small space debris impact induced discharge was presented.
This paper is about the study on small space debris effect on aircraft which carried out through the plasma accelerator. At the beginging of the study the plasma drag small particle accelector is under research which is very difficult as the first of this kind of accelector. On that instrument through experiments the method for accelerating small particle to 15km/s was obtained. During the research of the accelector the velocity measure of small hypervelocity particle is very important and the piezoelectricity method and laser method is developed and used in the accelector system other than that the brand new method based on hypervelocity impact plasma collection was developed. Experiment result indicates that this new method has high precision in velocity measurement, the single width is narrow and the cost is cheap so is a very good method.
The main work of this paper is about the hypervelocity impact experiment of small particle on solar cell cover glass and cumulative impact experiment of small particles on solar cell which carried out through the plasma drag small particle accelector. During the impact experiments on solar cell cover glass, through a lot experiment results the damage laws is acquired and the transmission rate on the damage area is measured. Using the damage equation and the Master2005 space debris model the method for evaluate the surface damage of solar cell is acquired. The caculated result through this method is fit for the result of similar calculation abroad. And through the calculation we found that particles with diameters between 5um and 500um make the main contribution to the surface damage. The power decline of the solar cell after the cumulative impact experiment is fit for with the calculation through the surface damage evaluation method. Although the result indicates that the transimission decay result from surface damge is the main reason of power decline. Further more the small space debris has little effect on solar cells.
At last the combined effect of small space debris impact and atomic oxygen and small space debris impact induced discharge was presented. Using plasma drag small particle accelector and PIG atomic oxygen instruments the experiment was carried out and the result inditacts that the combined effect is obvious and especially serious for Kapton material with defence coat,so it’s important to consider this combined effect. The first experiment about discharge induced through hypervelocity by particles with diameter in micron scale was carried out. So we should pay attention to those phenomena and to found out the essence of those phenomena and is effect to aircraft.
引文
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