The colonization of space

O'Neill, G.K.

doi:10.1063/1.3128863

Cited by 171 publications

(42 citation statements)

References 1 publication

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“…There is a group of enthusiasts who want to setup a colony at L 5 point of the Earth-Moon system. As already noted, because L 4 and L 5 are the stable points of equilibrium, they have been proposed for sites of large self-contained "Space colonies", an idea developed and advocated by the late O'Neill (1974). The three body problem have an interesting application for artificial satellites and future space colonization.…”

mentioning

confidence: 99%

Nonlinear stability in the generalised photogravitational restricted three body problem with Poynting-Robertson drag

Kushvah¹,

Sharma

Ishwar

2007

Astrophys Space Sci

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The Nonlinear stability of triangular equilibrium points has been discussed in the generalised photogravitational restricted three body problem with Poynting-Robertson drag. The problem is generalised in the sense that smaller primary is supposed to be an oblate spheroid. The bigger primary is considered as radiating. We have performed first and second order normalization of the Hamiltonian of the problem. We have applied KAM theorem to examine the condition of non-linear stability. We have found three critical mass ratios. Finally we conclude that triangular points are stable in the nonlinear sense except three critical mass ratios at which KAM theorem fails.

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mentioning

confidence: 99%

Nonlinear stability in the generalised photogravitational restricted three body problem with Poynting-Robertson drag

Kushvah¹,

Sharma

Ishwar

2007

Astrophys Space Sci

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“…The idea of using a fixed launcher rather than rocketry to move masses in the solar system has been discussed at least since the work of O'Neill [1]. There are more recent discussions in the literature of electromagnetic launchers for Earth applications [2][3][4] as well as lunar-based [5,6].…”

Section: Introductionmentioning

confidence: 99%

Mass Estimate for a Lunar Resource Launcher Based on Existing Terrestrial Electromagnetic Launchers

Roesler

2013

Machines

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Economic exploitation of lunar resources may be more efficient with a non-rocket approach to launch from the lunar surface. The launch system cost will depend on its design, and on the number of launches from Earth to deliver the system to the Moon. Both of these will depend on the launcher system mass. Properties of an electromagnetic resource launcher are derived from two mature terrestrial electromagnetic launchers. A mass model is derived and used to estimate launch costs for a developmental launch vehicle. A rough manufacturing cost for the system is suggested.

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“…In the case of Earth-Moon system, L 4 and L 5 points could be excellent locations to place space telescopes for astronomical observations or a space station (Schutz, 1977). In addition, Defilippi (1977) made a review of the ideas of American physicist Gerard K. O'Neill (O'Neill, 1974) about building space colonies at the L 4 and L 5 positions. These space stations could be used as a way-point for travelling to and from the region between Earth's atmosphere and the Moon (cis-lunar space).…”

Section: Introductionmentioning

confidence: 99%

Natural formations at the Earth–Moon triangular point in perturbed restricted problems

Salazar

Winter

Macau

et al. 2015

Advances in Space Research

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Previous studies for small formation flying dynamics about triangular libration points have determined the existence of regions of zero and minimum relative radial acceleration with respect to the nominal trajectory, that prevent from the expansion or contraction of the constellation. However, these studies only considered the gravitational force of the Earth and the Moon using the Circular Restricted Three Body Problem (CRTBP) scenario. Although the CRTBP model is a good approximation for the dynamics of spacecraft in the Earth-Moon system, the nominal trajectories around equilateral libration points are strongly affected when the primary orbit eccentricity and solar gravitational force are considered. In this manner, the goal of this work is the analysis of the best regions to place a formation that is flying close a bounded solution around L 4 , taking into account the Moon's eccentricity and Sun's gravity. This model is not only more realistic for practical engineering applications but permits to determine more accurately the fuel consumption to maintain the geometry of the formation.

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The colonization of space

Cited by 171 publications

References 1 publication

Nonlinear stability in the generalised photogravitational restricted three body problem with Poynting-Robertson drag

Nonlinear stability in the generalised photogravitational restricted three body problem with Poynting-Robertson drag

Mass Estimate for a Lunar Resource Launcher Based on Existing Terrestrial Electromagnetic Launchers

Natural formations at the Earth–Moon triangular point in perturbed restricted problems

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