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Deflection of fictitious asteroid 2017 PDC: Ion beam vs. kinetic impactor

机译：虚拟小行星2017 PDC的偏转：离子束与动力学撞击器

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摘要

Mission scenarios for the deflection of fictitious asteroid 2017 PDC are investigated. Two deflection options, kinetic impactor (KI) and ion beam shepherd (IBS), are studied and compared on the basis of deflection performance, safety, as well as mission schedule and political aspects. Firstly, we propose the launch of a medium-size rendevous spacecraft equipped with at least two ionic thrusters that can serve as propulsion means for the interplanetary trajectory up to rendezvous with the asteroid and as contactless actuators for a possible follow-up deflection mission. The asteroid, whose uncertainty ellipsoid is initially too large to establish whether (and how) it should be deflected, is reached by the rendezvous spacecraft after a low-thrust interplanetary trajectory of reasonable duration. Following rendezvous the spacecraft is placed in the vicinity of the asteroid to estimate its mass, study its structure and composition and, crucially, reduce its uncertainty ellipsoid by ground tracking to confirm or rule out an impact. Assuming that an impact is confirmed two main deflection scenarios are considered based on the actual asteroid size. Ion beam deflection is considered with the possibility of full deflection (the asteroid misses the Earth by a safe margin) or impact location adjustment (the impact footprint is diplaced to the nearest unpopulated region) depending on the asteroid size and the predicted impact location. The launch of a kinetic impactor mission is also considered with the employment of the rendezvous spacecraft to measure the deflection outcome and possibly to refine the deflection in case it is needed. The deflection performance of the two methods is compared.
机译：研究了虚拟小行星2017 PDC偏转的任务方案。根据偏转性能，安全性，任务进度和政治方面，研究并比较了两种偏转选项，即动力撞击器（KI）和离子束牧羊犬（IBS）。首先，我们建议发射一艘装备至少两个离子推进器的中型轮状航天器，该推进器可以用作行星际轨道直至与小行星会合的推进装置，并可以作为可能进行的后续偏转任务的非接触式致动器。小行星的不确定性椭球体最初太大，无法确定是否（以及如何偏转）小行星，交会航天器在合理持续时间的低推力行星际轨道之后到达了小行星。会合后，将航天器放置在小行星附近以估计其质量，研究其结构和组成，并且至关重要的是，通过地面跟踪以确认或排除影响来减小其不确定性椭球。假设已确认撞击，则根据实际小行星尺寸考虑两个主要的偏转情况。取决于小行星的大小和预计的撞击位置，认为离子束偏转有可能发生完全偏转（小行星以安全裕度错过地球）或进行碰撞位置调整（将撞击足迹转移到最近的无人区）。还考虑了动能撞击器任务的发射，并使用了交会航天器来测量偏转结果，并在必要时改进偏转。比较了两种方法的偏转性能。

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  • 来源
    《Acta astronautica》 |2019年第3期|301-307|共7页
  • 作者

    Bombardelli Claudio; Jose Calero Emilio; Luis Gonzalo Juan;

  • 作者单位

    Tech Univ Madrid, Pl Cardenal Cisneros 3, Madrid 28040, Spain|Space Dynam Grp, Madrid, Spain;

    Tech Univ Madrid, Pl Cardenal Cisneros 3, Madrid 28040, Spain|Space Dynam Grp, Madrid, Spain;

    Tech Univ Madrid, Pl Cardenal Cisneros 3, Madrid 28040, Spain|Space Dynam Grp, Madrid, Spain;

  • 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
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