立方体卫星制动帆装置离轨时间分析

发布时间：2018-03-21 22:05

本文选题：立方体卫星　切入点：制动帆装置　出处：《航天器工程》2016年03期 　论文类型：期刊论文

【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。
[Abstract]:In order to prevent CubeSats from becoming space debris after their failure, low-cost brake sail devices should be used at the end of the CubeSata life to get them out of orbit quickly, In order to reduce the threat of collision and damage to Leo) spacecraft, the mathematical model of Cube-satellite deorbiting is established in this paper, and the influence factors of Cube-satellite deorbiting time are obtained, respectively, such as cubic satellite surface-mass ratio. The influence of the above three influencing factors on the deorbiting time is analyzed by using an example. The results show that with the increase of the surface mass ratio of the cube satellite, the deorbiting time decreases continuously, the higher the orbital height, the longer the deorbiting time. The time of deorbiting also varies greatly with different launching dates. The time of detaching from orbit is short in the peak year of solar activity and long in the low year of solar activity. According to the analysis results, the braking sail area can be designed to be 4mm2 for the 3U cubic satellite.
【作者单位】：南京理工大学机械工程学院;
【基金】：江苏省普通高校研究生科研创新计划项目(KYLX15_0343)
【分类号】：V528

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