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首页> 外文学位 >A feasibility study on the implementation of satellite-to-satellite tracking around a small near-Earth object.
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A feasibility study on the implementation of satellite-to-satellite tracking around a small near-Earth object.

机译：关于在一个小的近地天体周围实施卫星到卫星跟踪的可行性研究。

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摘要

Near-earth objects (NEOs) are asteroids and comets that have a perihelion distance of less than 1.3 astronomical units (AU). There are currently more than 10,000 known NEOs. The majority of these objects are less than 1 km in diameter. Despite the number of NEOs, little is known about most of them. Characterizing these objects is a crucial component in developing a thorough understanding of solar system evolution, human exploration, exploitation of asteroid resources, and threat mitigation. Of particular interest is characterizing the internal structure of NEOs. While ground-based methods exist for characterizing the internal structure of NEOs, the information that can be gleaned from such studies is limited and often accompanied by large uncertainty. An alternative is to use in situ studies to examine an NEO's shape and gravity field, which can be used to assess its internal structure.;This thesis investigates the use of satellite-to-satellite tracking (SST) to map the gravity field of a small NEO on the order of 500 m or less. An analysis of the mission requirements of two previously flown SST missions, GRACE and GRAIL, is conducted. Additionally, a simulation is developed to investigate the dynamics of SST in the vicinity of a small NEO. This simulation is then used to simulate range and range-rate data in the strongly perturbed environment of the small NEO. These data are used in conjunction with the analysis of the GRACE and GRAIL missions to establish a range of orbital parameters that can be used to execute a SST mission around a small NEO. Preliminary mission requirements for data collection and orbital correction maneuvers are also established. Additionally, the data are used to determine whether or not proven technology can be used to resolve the expected range and range-rate measurements.;It is determined that the orbit semi-major axis for each spacecraft should be approximately 100% to 200% of the NEO's mean diameter and the two spacecraft should be in circular, near polar orbits. This configuration will produce trajectories, which exhibit reasonable stability over a period of roughly 24 hours. Corrective maneuvers will therefore be required with a frequency of approximately once per day. Due to the potentially rapid changes caused by the highly perturbed environment, it is likely that these maneuvers will need to be made autonomously. During the period between corrective maneuvers SST data collection will be possible. The expected range and range-rate measurements will be on the order of +/-10-5 m and +/-10 -5 m/s respectively and can be resolved using proven technology.
机译：近地天体（NEO）是小行星和彗星，其近日点距离小于1.3天文单位（AU）。当前有10,000多个已知的NEO。这些物体中的大多数直径小于1 km。尽管NEO数量众多，但对大多数人知之甚少。对这些物体进行特征描述是全面了解太阳系演化，人类探索，小行星资源开发和缓解威胁的关键组成部分。特别令人感兴趣的是表征NEO的内部结构。尽管存在基于地面的方法来表征近地天体的内部结构，但可以从此类研究中收集到的信息有限，并且常常伴随着很大的不确定性。一种替代方法是使用原位研究来检查NEO的形状和重力场，从而可以评估其内部结构。;本文研究了使用卫星到卫星跟踪（SST）绘制卫星的重力场的方法。约500 m或更小的小型NEO。对以前执行过的两个SST任务GRACE和GRAIL的任务要求进行了分析。另外，开发了一个模拟来研究小型NEO附近SST的动力学。然后，该模拟用于在小型NEO强烈干扰的环境中模拟范围和范围率数据。这些数据与GRACE和GRAIL任务的分析结合使用，可建立一系列轨道参数，这些参数可用于围绕小型NEO执行SST任务。还确定了数据收集和轨道校正操作的初步任务要求。此外，该数据还用于确定是否可以使用经过验证的技术来解决预期的范围和测距率测量结果;确定每个航天器的轨道半长轴应约为其的100％至200％ NEO的平均直径和两个航天器应为圆形，并接近极地轨道。这种配置将产生轨迹，该轨迹在大约24小时的时间内显示出合理的稳定性。因此，将需要大约每天一次的纠正措施。由于高度扰动的环境可能会导致快速变化，因此可能需要自动进行这些操作。在两次纠正操作之间，可能会收集SST数据。预期的范围和范围率测量值分别为+/- 10-5 m和+/- 10 -5 m / s，可以使用成熟的技术解决。

著录项

  • 作者

    Church, Christopher J.;

  • 作者单位

    The University of North Dakota.;

  • 授予单位 The University of North Dakota.;
  • 学科 Aerospace engineering.
  • 学位 M.S.
  • 年度 2014
  • 页码 154 p.
  • 总页数 154
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

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