Numerical study about natural escape and capture routes by the Moon via Lagrangian points L1 and L2

<p>In this study, we use a combination of 3D Particle-in-Cell (PIC) simulations and a laboratory experiment to investigate the dynamics of solar wind - Moon interaction. It is known that the Moon has no global magnetic field, but there exist areas of intense remanent magnetization of the lunar crust which are strongly non-dipolar. Performed simulations indicate that the localized crustal fields are capable of scattering solar wind ions, efficiently heat electrons, and produce magnetic field perturbations in the upstream plasma. Numerical study of reflected ion flux compares well to the laboratory experiment performed at induction discharge theta-pinch "KI-1" facility (Novosibirsk). The plasma flow interacts with a magnetic field source (dipolar or quadrupolar), producing a minimagnetosphere with typical scales comparable to (or less than) a few ion inertial lengths. Our numerical and laboratory study concludes that the magnetic field should drop faster than r<sup>-3</sup> with the distance in order to reproduce the spacecraft observations. In this case, gyroradii of the reflected ions are considerably larger than the scale of the minimagnetosphere density cavity. Reflected ions generate enhancements in the upstream magnetic field, supposedly seen as LEMEs (lunar external magnetic enhancements) in spacecraft data above the Moon crustal fields.</p>

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Numerical study of low-cost alternative orbits around the Moon

Advances in Space Research ◽

10.1016/j.asr.2005.07.052 ◽

2005 ◽

Vol 36 (3) ◽

pp. 552-560 ◽

Cited By ~ 5

Author(s):

C.F. de Melo ◽

O.C. Winter ◽

E. Vieira Neto

Keyword(s):

Numerical Study ◽

Low Cost ◽

The Moon

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CONSTRUCTING AN OPTICAL LUNAR NAVIGATION SYSTEM BASED ON SPACECRAFT MADE BY LAVOCHKIN ASSOCIATION

Space engineering and technology ◽

10.33950/spacetech-2308-7625-2019-4-12-26 ◽

2019 ◽

pp. 12-26

Author(s):

A.V. BAGROV ◽

A.O. DMITRIEV ◽

V.A. LEONOV ◽

I.V. MOSKATINYEV ◽

V.K. SYSOEV ◽

...

Keyword(s):

Navigation System ◽

Artificial Satellite ◽

Optimal Solution ◽

Optical Navigation ◽

Space Systems ◽

The Moon ◽

Lagrange Points ◽

Global Positioning ◽

L1 And L2 ◽

Communications System

The paper discusses the problem of developing an optical system for global positioning on the Moon to within one meter designed to service a limited number of users. It was demonstrated that the optimal solution of the problem would be to continuously monitor the positions of laser light beacons on the lunar surface from on-board an artificial satellite of the Moon equipped with an onboard TV camera, as well as from onboard a spacecraft placed at the L1 and L2 Lagrange points of the Earth-Moon system. The paper demonstrates the feasibility of a global lunar optical navigation and communications system based on space systems projects that are being developed at NPO Lavochkin: Spektr-UV observatory, lunar spacecraft Luna-25 and Luna-26. The use of these space systems will make it possible to start working in realistic terms on the navigation/communications system as a part of the future engineering infrastructure for lunar exploration. Keywords: telescope, optical navigation system, lunar base, Lagrange point, Spektr-UV, Luna-25, Luna-26.

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Planetary defense from the nearest 4 lagrangian points plus rfi-free radioastronomy from the farside of the moon: a unified vision

Acta Astronautica ◽

10.1016/s0094-5765(01)00176-x ◽

2002 ◽

Vol 50 (3) ◽

pp. 185-199 ◽

Cited By ~ 12

Author(s):

Claudio Maccone

Keyword(s):

The Moon ◽

Lagrangian Points ◽

Planetary Defense

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The motion of a lunar orbiter

Symposium - International Astronomical Union ◽

10.1017/s0074180900105686 ◽

1966 ◽

Vol 25 ◽

pp. 373

Author(s):

Y. Kozai

Keyword(s):

Degrees Of Freedom ◽

Dimensional Space ◽

Artificial Satellite ◽

Equations Of Motion ◽

Triaxial Ellipsoid ◽

The Moon ◽

Secular Motion ◽

The Earth ◽

Close Satellite ◽

The Mean

The motion of an artificial satellite around the Moon is much more complicated than that around the Earth, since the shape of the Moon is a triaxial ellipsoid and the effect of the Earth on the motion is very important even for a very close satellite.The differential equations of motion of the satellite are written in canonical form of three degrees of freedom with time depending Hamiltonian. By eliminating short-periodic terms depending on the mean longitude of the satellite and by assuming that the Earth is moving on the lunar equator, however, the equations are reduced to those of two degrees of freedom with an energy integral.Since the mean motion of the Earth around the Moon is more rapid than the secular motion of the argument of pericentre of the satellite by a factor of one order, the terms depending on the longitude of the Earth can be eliminated, and the degree of freedom is reduced to one.Then the motion can be discussed by drawing equi-energy curves in two-dimensional space. According to these figures satellites with high inclination have large possibilities of falling down to the lunar surface even if the initial eccentricities are very small.The principal properties of the motion are not changed even if plausible values ofJ3andJ4of the Moon are included.This paper has been published in Publ. astr. Soc.Japan15, 301, 1963.

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