scholarly journals Orbit of a lunar artificial satellite: Analytical theory of perturbations

2004 ◽  
Vol 2004 (IAUC196) ◽  
pp. 254-262 ◽  
Author(s):  
B. De Saedeleer ◽  
J. Henrard
Keyword(s):  
Artificial Satellite ◽  
Analytical Theory ◽  
Lunar Artificial Satellite

scholarly journals Nonsphericity of the Moon and Near Sun-Synchronous Polar Lunar Orbits

2009 ◽  
Vol 2009 ◽  
pp. 1-24 ◽  
Author(s):  
Jean Paulo dos Santos Carvalho ◽  
Rodolpho Vilhena de Moraes ◽  
Antônio Fernando Bertachini de Almeida Prado
Keyword(s):  
Numerical Simulations ◽  
Artificial Satellite ◽  
Nonuniform Distribution ◽  
Second Order ◽  
The Moon ◽  
Disturbing Potential ◽  
Short Period ◽  
Coupling Terms ◽  
Lunar Artificial Satellite ◽  
Hori Method

Herein, we consider the problem of a lunar artificial satellite perturbed by the nonuniform distribution of mass of the Moon taking into account the oblateness (J2) and the equatorial ellipticity (sectorial termC22). Using Lie-Hori method up to the second order short-period terms of the Hamiltonian are eliminated. A study is done for the critical inclination in first and second order of the disturbing potential. Coupling terms due to the nonuniform distribution of mass of the Moon are analyzed. Numerical simulations are presented with the disturbing potential of first and second order is. It an approach for the behavior of the longitude of the ascending node of a near Sun-synchronous polar lunar orbit is presented.

Analytical Theory of an Artificial Satellite of the Moon

2004 ◽  
Vol 1017 (1) ◽  
pp. 434-449 ◽  
Author(s):  
BERNARD DE SAEDELEER ◽  
JACQUES HENRARD
Keyword(s):  
Artificial Satellite ◽  
Analytical Theory ◽  
The Moon

FROZEN ORBITS AROUND EUROPA

2012 ◽  
Vol 22 (10) ◽  
pp. 1250240 ◽  
Author(s):  
J. P. S. CARVALHO ◽  
D. C. MOURÃO ◽  
A. ELIPE ◽  
R. VILHENA DE MORAES ◽  
A. F. B. A. PRADO
Keyword(s):  
Artificial Satellite ◽  
Analytical Theory ◽  
Third Body ◽  
Planetary Satellite ◽  
Frozen Orbits ◽  
Satellites Of Jupiter ◽  
Long Lifetime ◽  
Low Altitude ◽  
Natural Satellites ◽  
Averaged Model

Low-altitude, near-polar orbits are very desirable for scientific missions to study the natural satellites of the planets of the Solar System, such as Europa, that is one of the natural satellites of Jupiter. The problem is analyzed considering that an artificial satellite is orbiting Europa and that this spacecraft is perturbed by the nonuniform distribution of mass of the planetary satellite (J2, J3, C22) and by the gravitational attraction of the third-body. We present an analytical theory using the averaged model and applications were done by performing numerical integrations of the analytical equations developed. Using the averaged method, several frozen orbits were obtained. Some of them has low inclination, low altitude and long lifetime. Numerical simulations are performed using the software Mercury, to compare the results obtained using the analytical theory.

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.

Sign in / Sign up

Export Citation Format

Share Document