摘要
为了避免立方体卫星(CubeSat)失效后成为空间碎片,在立方体卫星寿命末期应采用低成本制动帆装置使其快速脱离轨道,从而减少对低地球轨道(LEO)航天器碰撞和损坏的威胁。文章建立了立方体卫星离轨的数学模型,得到立方体卫星离轨时间的影响因素分别为立方体卫星面质比、轨道高度和发射日期。应用实例仿真分析上述3种影响因素对离轨时间的影响,结果表明:随着立方体卫星面质比的增加,离轨时间不断减少;轨道高度越高,离轨时间越长;发射日期不同,离轨时间也存在较大的差异,在太阳活动峰年时离轨时间短,在太阳活动低年时离轨时间长。根据分析结果,对于3U立方体卫星而言,制动帆面积可设计为4m^2。
To avoid a non-functional CubeSat becoming space debris,it is necessary to use a lowcost drag sail device as an end-of-life disposal which makes the CubeSat deorbit quickly and decreases the threat of collisions and damages to other spacecraft.A CubeSat de-orbiting mathematical model is established,and the factors influencing de-orbiting time are obtained such as areamass radio,orbit altitude and launch date.Some examples are used to analyze these factors,and the simulation results show that the area-mass ratio of CubeSat has high influence on the de-orbiting time.The greater area-mass ratio is,the shorter de-orbiting time is.Also,the de-orbiting time increases as the orbit altitude is increasing.What＇s more,the de-orbiting time of a CubeSat can vary depending on launch date that high solar activity gives lower de-orbiting time and low solar activity gives longer de-orbiting time.According to the results of the analysis,a drag sail device with a deployed areas of 4m^2 is designed for a 3U CubeSat.
出处
《航天器工程》
北大核心
2016年第3期26-31,共6页
Spacecraft Engineering
基金
江苏省普通高校研究生科研创新计划项目(KYLX15_0343)
