Maccone Claudio
International Academy of Astronautics, Torino, Italy.
Ann N Y Acad Sci. 2004 May;1017:370-85. doi: 10.1196/annals.1311.020.
Software code named asteroff was recently created by the author to simulate the deflection of hazardous asteroids off of their collision course with the Earth. This code was both copyrighted and patented to avoid unauthorized use of ideas that could possibly be vital to construct a planetary defense system in the vicinity of the Earth. Having so said, the basic ideas and equations underlying the asteroff simulation code are openly described in this paper. A system of two space bases housing missiles is proposed to achieve the planetary defense of the Earth against dangerous asteroids and comets, collectively called impactors herein. We show that the layout of the Earth-Moon system with the five relevant Lagrangian (or libration) points in space leads naturally to only one, unmistakable location of these two space bases within the sphere of influence of the Earth. These locations are at the two Lagrangian points L(1) (between the Earth and the Moon) and L(3) (in the direction opposite to the Moon from the Earth). We show that placing missile bases at L(1) and L(3) would enable those missiles to deflect the trajectory of impactors by hitting them orthogonally to their impact trajectory toward the Earth, so as to maximize their deflection. We show that confocal conics are the best class of trajectories fulfilling this orthogonal deflection requirement. One additional remark is that the theory developed in this paper is just a beginning for a wider set of future research. In fact, we only develop the Keplerian analytical theory for the optimal planetary defense achievable from the Earth-Moon Lagrangian points L(1) and L(3). Much more sophisticated analytical refinements would be needed to: (1) take into account many perturbation forces of all kinds acting on both the impactors and missiles shot from L(1) and L(3); (2) add more (non-optimal) trajectories of missiles shot from either the Lagrangian points L(4) and L(5) of the Earth-Moon System or from the surface of the Moon itself; and (3) encompass the full range of missiles currently available to the US (and possibly other countries) so as to really see which impactors could be diverted by which missiles, even in the very simplified scheme outlined here. Published for the first time in February 2002, our Keplerian planetary defense theory has proved, in just one year, to be simple enough to catch the attention of scholars, in addition to popular writers, and even of someone from the US Military. These recent developments might possibly mark the beginning of an all embracing vision in planetary defense beyond all learned congressional activities, dramatic movies, and unknown military plans covered by secrecy.
作者最近创建了名为asteroff的软件代码,用于模拟危险小行星偏离其与地球碰撞轨道的情况。该代码已获得版权和专利,以避免未经授权使用可能对构建地球附近的行星防御系统至关重要的想法。话虽如此,本文公开描述了asteroff模拟代码背后的基本思想和方程。本文提出了一个由两个容纳导弹的太空基地组成的系统,以实现地球对危险小行星和彗星(本文统称为撞击体)的行星防御。我们表明,具有五个相关拉格朗日(或平动)点的地月系统布局自然地导致这两个太空基地在地球影响范围内只有一个明确无误的位置。这些位置位于两个拉格朗日点L(1)(在地球和月球之间)和L(3)(在从地球到月球相反的方向上)。我们表明,将导弹基地放置在L(1)和L(3)将使这些导弹能够通过与撞击体朝向地球的撞击轨迹正交撞击来偏转其轨迹,从而使其偏转最大化。我们表明,共焦圆锥曲线是满足这种正交偏转要求的最佳轨迹类别。另一个需要说明的是,本文中发展的理论只是更广泛的未来研究的一个开端。事实上,我们仅为从地月拉格朗日点L(1)和L(3)实现的最优行星防御发展了开普勒分析理论。要做到以下几点还需要更复杂的分析改进:(1)考虑作用在撞击体以及从L(1)和L(3)发射的导弹上的各种摄动力;(2)增加从地月系统的拉格朗日点L(4)和L(5)或从月球表面发射的导弹的更多(非最优)轨迹;(3)涵盖美国(可能还有其他国家)目前可用的所有导弹,以便即使在此处概述的非常简化的方案中,也能真正了解哪些撞击体可以被哪些导弹偏转。我们的开普勒行星防御理论于2002年2月首次发表,仅在一年时间里就证明足够简单,不仅引起了学者的关注,还吸引了通俗作家甚至美国军方人员的注意。这些最新进展可能标志着超越所有学术性的国会活动、戏剧性电影以及被保密的未知军事计划的全面行星防御愿景的开端。