Research Of Small Space Debris Impact Effect

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.