scholarly journals Optimal Low Thrust Trajectories to the Moon

2003 ◽  
Vol 2 (2) ◽  
pp. 144-170 ◽  
Author(s):  
John T. Betts ◽  
Sven O. Erb
Keyword(s):  
The Moon ◽  
Low Thrust

Rapid Design and Exploration of High-Fidelity Low-Thrust Transfers to the Moon

2020 ◽  
Author(s):  
Jackson Shannon ◽  
Martin Ozimek ◽  
Justin Atchison ◽  
Christine Hartzell
Keyword(s):  
High Fidelity ◽  
The Moon ◽  
Low Thrust ◽  
Rapid Design

Efficient invariant-manifold, low-thrust planar trajectories to the Moon

2012 ◽  
Vol 17 (2) ◽  
pp. 817-831 ◽  
Author(s):  
G. Mingotti ◽  
F. Topputo ◽  
F. Bernelli-Zazzera
Keyword(s):  
Invariant Manifold ◽  
The Moon ◽  
Low Thrust

Low-energy, low-thrust transfers to the Moon

2009 ◽  
Vol 105 (1-3) ◽  
pp. 61-74 ◽  
Author(s):  
G. Mingotti ◽  
F. Topputo ◽  
F. Bernelli-Zazzera
Keyword(s):  
Low Energy ◽  
The Moon ◽  
Low Thrust

scholarly journals Controlling the Eccentricity of Polar Lunar Orbits with Low-Thrust Propulsion

2009 ◽  
Vol 2009 ◽  
pp. 1-10 ◽  
Author(s):  
O. C. Winter ◽  
D. C. Mourão ◽  
C. F. de Melo ◽  
E. N. Macau ◽  
J. L. Ferreira ◽  
...  
Keyword(s):  
Body Problem ◽  
Earth Satellite ◽  
The Moon ◽  
Low Thrust ◽  
Orbital Eccentricity ◽  
High Increase ◽  
Empirical Expression ◽  
Body Model ◽  
Hall Plasma ◽  
Kozai Resonance

It is well known that lunar satellites in polar orbits suffer a high increase on the eccentricity due to the gravitational perturbation of the Earth. That effect is a natural consequence of the Lidov-Kozai resonance. The final fate of such satellites is the collision with the Moon. Therefore, the control of the orbital eccentricity leads to the control of the satellite's lifetime. In the present work we study this problem and introduce an approach in order to keep the orbital eccentricity of the satellite at low values. The whole work was made considering two systems: the 3-body problem, Moon-Earth-satellite, and the 4-body problem, Moon-Earth-Sun-satellite. First, we simulated the systems considering a satellite with initial eccentricity equals to 0.0001 and a range of initial altitudes between 100 km and 5000 km. In such simulations we followed the evolution of the satellite's eccentricity. We also obtained an empirical expression for the length of time needed to occur the collision with the Moon as a function of the initial altitude. The results found for the 3-body model were not significantly different from those found for the 4-body model. Secondly, using low-thrust propulsion, we introduced a correction of the eccentricity every time it reached the value 0.05. These simulations were made considering a set of different thrust values, from 0.1 N up to 0.4 N which can be obtained by using Hall Plasma Thrusters. In each run we measured the length of time, needed to correct the eccentricity value (frome=0.04toe=0.05). From these results we obtained empirical expressions of this time as a function of the initial altitude and as a function of the thrust value.

Lyapunov-based low-energy low-thrust transfers to the Moon

2019 ◽  
Vol 162 ◽  
pp. 87-97 ◽  
Author(s):  
R. Epenoy ◽  
D. Pérez-Palau
Keyword(s):  
Low Energy ◽  
The Moon ◽  
Low Thrust

A Method to Design Efficient Low-Energy, Low-Thrust Transfers to the Moon

2011 ◽  
pp. 15-37 ◽  
Author(s):  
Giorgio Mingotti ◽  
Francesco Topputo ◽  
Franco Bernelli-Zazzera
Keyword(s):  
Low Energy ◽  
The Moon ◽  
Low Thrust

The motion of a lunar orbiter

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.

Laboratory Simulation of Lunar Luminescence

1962 ◽  
Vol 14 ◽  
pp. 441-444 ◽  
Author(s):  
J. E. Geake ◽  
H. Lipson ◽  
M. D. Lumb
Keyword(s):  
Science And Technology ◽  
Laboratory Simulation ◽  
The Moon ◽  
Physics Department ◽  
Luminescent Spectrum

Work has recently begun in the Physics Department of the Manchester College of Science and Technology on an attempt to simulate lunar luminescence in the laboratory. This programme is running parallel with that of our colleagues in the Manchester University Astronomy Department, who are making observations of the luminescent spectrum of the Moon itself. Our instruments are as yet only partly completed, but we will describe briefly what they are to consist of, in the hope that we may benefit from the comments of others in the same field, and arrange to co-ordinate our work with theirs.

Formation of Lunar Craters and Bright Rays as a Result of Meteorite Impacts

1962 ◽  
Vol 14 ◽  
pp. 415-418
Author(s):  
K. P. Stanyukovich ◽  
V. A. Bronshten
Keyword(s):  
Explosive Charge ◽  
The Moon ◽  
Meteorite Impacts ◽  
The Earth ◽  
Lunar Craters ◽  
The Impact

The phenomena accompanying the impact of large meteorites on the surface of the Moon or of the Earth can be examined on the basis of the theory of explosive phenomena if we assume that, instead of an exploding meteorite moving inside the rock, we have an explosive charge (equivalent in energy), situated at a certain distance under the surface.

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