A lunar exploration architecture using lunar libration point one

Yazdi, Kian; Messerschmid, Ernst

doi:10.1016/j.ast.2007.06.001

Cited by 8 publications

(5 citation statements)

References 6 publications

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“…The Cislunar environment is a promising location for future space exploration architectures, both crewed and robotic. Recent studies and the Global Exploration Roadmap [1,2] highlighted the benefits of a support infrastructure located in such an environment, leveraging the dynamical features offered by non-Keplerian multi-body orbits. Among those, the family of Near Rectilinear Halo Orbits (NRHO), in particular, appears specifically suitable to stage a human-robotic exploration outpost [3].…”

Section: Introductionmentioning

confidence: 99%

Guidance, navigation and control for 6DOF rendezvous in Cislunar multi-body environment

Colagrossi

Pesce

Bucci

et al. 2021

Aerospace Science and Technology

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Section: Introductionmentioning

confidence: 99%

Guidance, navigation and control for 6DOF rendezvous in Cislunar multi-body environment

Colagrossi

Pesce

Bucci

et al. 2021

Aerospace Science and Technology

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“…[4,11,15,18,30,33]) but has received recently a renewal of interest, in view of new space missions possibly involving a lunar space station (see e.g. [17,26,28,36,41]). …”

Section: Local Lyapunov Exponentsmentioning

confidence: 99%

Eight-shaped Lissajous orbits in the Earth-Moon system

Archambeau¹,

Augros²,

Trélat³

2011

MathS In A.

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Euler and Lagrange proved the existence of five equilibrium points in the circular restricted three-body problem. These equilibrium points are known as the Lagrange points (Euler points or libration points) L1, . . . , L5. The existence of families of periodic and quasi-periodic orbits around these points is well known (see [20,21,22,23,37]). Among them, halo orbits are 3-dimensional periodic orbits diffeomorphic to circles. They are the first kind of the so-called Lissajous orbits. To be selfcontained, we first provide a survey on the circular restricted three-body problem, recall the concepts of Lagrange point and of periodic or quasi-periodic orbits, and recall the mathematical tools in order to show their existence. We then focus more precisely on Lissajous orbits of the second kind, which are almost vertical and have the shape of an eight -we call them eight-shaped Lissajous orbits. Their existence is also well known, and in the Earth-Moon system, we first show how to compute numerically a family of such orbits, based on Linsdtedt Poincaré's method combined with a continuation method on the excursion parameter. Our original contribution is in the investigation of their specific stability properties. In particular, using local Lyapunov exponents we produce numerical evidences that their invariant manifolds share nice global stability properties, which make them of interest in space mission design. More precisely, we show numerically that invariant manifolds of eight-shaped Lissajous orbits keep in large time a structure of eight-shaped tubes. This property is compared with halo orbits, the invariant manifolds of which do not share such global stability properties. Finally, we show that the invariant manifolds of eight-shaped Lissajous orbits (viewed in the Earth-Moon system) can be used to visit almost all the surface of the Moon.

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“…The L 2 Lagrangian point is located 36,900 mi (61,500 km) beyond the lunar farside on the Earth-Moon vector. Lunar orbits at L 1 and L 2 are referred to as LLI and LL2 orbits, respec-tively (Yazdi and Messerschmid, 2008). An efficient lunar mining and settlement architecture involving minimal delta-v costs would include a space depot in an LLI orbit.…”

Section: Technical and Economic Constraints On Locations Of Lunar Facmentioning

confidence: 99%

“…A polar Moon base would require a slightly higher delta-v cost (up to $200 ft/s [$60 m/s]) to access from a lunar station in an LL1 or LL2 orbit than would an equatorial Moon base (Farquhar, 1972;Marsden and Ross, 2005). The LL1 and LL2 are defined as lunar orbits accessing the quasi-stable Lagrangian points L 1 and L 2 , respectively (Yazdi and Messerschmid, 2008). In addition, the delta-v cost for transfer between a 60 mi (96 km) polar lunar orbit and an equatorial landing site linked to a space depot at L 1 and L 2 would be at least 3000 ft/s (915 m/s) (Faust, 1970).…”

Section: Polar Regionsmentioning

confidence: 99%

“…Nearside equatorial areas have traditionally been considered as sites for lunar settlements and landing sites, considering that most of the Apollo missions visited these areas and that they are readily accessible from nonpolar LLOs (Yazdi and Messerschmid, 2008). Some equatorial areas are relatively enriched in titanium-bearing basalts rich in ilmenite and helium-3 deposits in Mare Tranquillitatis, Mare Marginis, and isolated areas in the southern part of Oceanus Procellarum (Schmitt, 2006).…”

Section: Nearside Equatorial Regionsmentioning

confidence: 99%

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The Significance of Lunar Water Ice and Other Mineral Resources for Rocket Propellants and Human Settlement of the Moon

Ambrose¹

Energy Resources for Human Settlement in the Solar System and Earth’s Future in Space

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F uture success in exploration and human habitation of the solar system will depend on space missions and settlements becoming more self-sustaining through exploitation of extraterrestrial (i.e., local) energy and material resources. For example, the Moon contains a wide variety of energy minerals and other resources that can potentially be used for manufacture of propellants for space transportation, volatiles for manufacture of chemicals, and metals for construction of solar power facilities, industrial plants, and structures for human habitation. If water ice in polar regions on the Moon is proven to exist in large quantities, these resources could not only support human habitation but could also be used to manufacture rocket propellants, reducing dependency on Earth for these resources, thereby making human space exploration more economically viable. Moreover, the lower gravity well of the Moon could be used as a launching site for missions to Mars and other worlds in the solar system, given the possibility of water-ice and other lunar resources. New exploration tools will need to be developed to fully and accurately characterize the potential lunar resource base. For example, detection and quantification of suspected water-ice resource in lunar polar regions in recent missions involve an array of technologies not commonly used in hydrocarbon exploration on Earth, such as synthetic aperture radar, epithermal neutron detectors, and imaging of reflected ultraviolet starlight using Lyman-alpha scattering properties. Optimal locations for potential lunar bases and industrial facilities reflect several factors that include the distribution of water ice, volatiles (nitrogen), nuclear materials (helium-3, thorium, and uranium), and metals (titanium, magnesium, and iron). Other important factors are the duration of insolation (sunlight), where solar power facilities could be constructed in polar

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A lunar exploration architecture using lunar libration point one

Cited by 8 publications

References 6 publications

Guidance, navigation and control for 6DOF rendezvous in Cislunar multi-body environment

Guidance, navigation and control for 6DOF rendezvous in Cislunar multi-body environment

Eight-shaped Lissajous orbits in the Earth-Moon system

The Significance of Lunar Water Ice and Other Mineral Resources for Rocket Propellants and Human Settlement of the Moon

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