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Orbital lifetime and collision risk reduction for inclined geosynchronous disposal orbits

机译：倾斜地球同步处置轨道的轨道寿命和碰撞风险降低

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摘要

A growing number of satellites are operating on inclined geosynchronous orbits (IGSOs) with inclination typically much higher than that of traditional geosynchronous orbits (GEOs). Several recent studies have considered the long-term evolution of IGSOs. Unlike traditional GEO disposal orbits, IGSO disposal orbits can undergo large excursions in eccentricity due to the effect of luni-solar gravity perturbations. For specific ranges of initial orbital elements, perigee can reach the Earth's atmosphere, resulting in vehicle reentry. A previously published study by the authors on Tundra orbits, a specific class of IGSO with critical inclination and moderate eccentricity, demonstrated that orbital lifetime can be reduced below 200 years (in some cases below 25 years) and that the corresponding collision probability with background objects can be significantly reduced below that for traditional GEO disposal orbits. This paper presents a study of a broad range of IGSO disposal orbits. Three cases of IGSO disposal orbit were considered: (1) near circular orbits (motivated by the BeiDou and IRNSS constellations); (2) orbits with intermediate eccentricity (motivated by the QZS constellation); and (3) orbits with larger eccentricity (motivated by the Sirius Tundra constellation). For each case, a large number of long-term propagations using the high-precision code TRACE were performed. Disposal orbit initial inclination and right ascension of ascending node (RAAN) were parametrically varied. The Aerospace Debris Environment Projection Tool (ADEPT) suite was used to determine collision probability with inactive background objects and with operational satellites in GEO, medium Earth orbit (MEO), and low Earth orbit (LEO). Study results show that orbital lifetime of IGSOs can be reduced to less than 200 years for all three IGSO cases considered if initial inclination is high enough. The minimum required inclination depends on initial RAAN. An orbital lifetime less than 200 years offers effective reduction of probability of collision with inactive background objects (by 0.7-1.8 orders of magnitude) and can be achieved in a wider disposal orbit design space than would be needed to reduce orbital lifetime to less than 25 years. For near circular IGSOs, collision probability with operational satellites will be higher at high inclinations than at low inclinations, but there are options for mitigation. When inclination is not high enough to achieve reentry, a high eccentricity storage disposal orbit may be a consideration if collision probability is lower than for other options.
机译：越来越多的卫星在倾斜的地球同步轨道（IGSO）上运行，其倾斜度通常比传统地球同步轨道（GEO）的倾斜度高得多。最近的一些研究已经考虑了IGSO的长期发展。与传统的GEO弃置轨道不同，IGSO弃置轨道可能由于太阳单轴重力扰动的影响而发生大的偏心偏移。对于特定范围的初始轨道元素，近地点可以到达地球大气层，从而导致飞行器重新进入。作者先前发表的关于Tundra轨道的研究，Tundra轨道是一类具有临界倾角和中度偏心的IGSO，证明轨道寿命可以降低到200年以下（在某些情况下是25年以下），并且与背景物体发生碰撞的概率也相应降低可以大大减少，低于传统的GEO处置轨道。本文介绍了广泛的IGSO处置轨道研究。考虑了IGSO弃置轨道的三种情况：（1）在圆形轨道附近（受北斗和IRNSS星座驱动）； （2）具有中等偏心率的轨道（由QZS星座驱动）； （3）偏心率较大的轨道（由Sirius Tundra星座驱动）。对于每种情况，都使用高精度代码TRACE进行了大量的长期传播。弃置轨道的初始倾角和上升节点的右升（RAAN）在参数上有所不同。航空航天碎片环境投影工具（ADEPT）套件用于确定与非活动背景物体以及与GEO，中地球轨道（MEO）和低地球轨道（LEO）中的运行卫星的碰撞概率。研究结果表明，如果初始倾斜度足够高，那么考虑到的所有三种IGSO情况，IGSO的轨道寿命都可以缩短至不到200年。所需的最小倾斜度取决于初始RAAN。小于200年的轨道寿命有效降低了与非活动本底物体发生碰撞的可能性（降低了0.7-1.8个数量级），并且可以在比将轨道寿命缩短至小于25所需的更宽的轨道设计空间中实现年份。对于接近圆形的IGSO，与运行卫星的碰撞概率在高倾角处比在低倾角处更高，但是有缓解的选择。当倾斜度不足以实现折返时，如果碰撞概率低于其他选项，则可以考虑使用高偏心率存储处置轨道。

著录项

  • 来源
    《Acta astronautica》 |2019年第8期|153-165|共13页
  • 作者

    Jenkin Alan B.; McVey John P.; Sorge Marlon E.;

  • 作者单位

    Aerosp Corp, Astrodynam Dept, POB 92957, Los Angeles, CA 90009 USA;

    Aerosp Corp, Astrodynam Dept, POB 92957, Los Angeles, CA 90009 USA;

    Aerosp Corp, Astrodynam Dept, 2155 Louisiana Blvd NE,Suite 5000, Albuquerque, NM 87110 USA;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    Orbital debris; Disposal; Dynamics; Collision risk;

    机译：轨道碎片;处置;动力学;碰撞风险;

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