Applications of a Solution of the regularized equations of motion of the restricted problem

1966 ◽  
Vol 71 ◽  
pp. 562
Author(s):  
David A. Pierce
Keyword(s):  
Restricted Problem ◽  
Equations Of Motion

scholarly journals Periodic orbits in the restricted problem of three bodies in a three-dimensional coordinate system when the smaller primary is a triaxial rigid body

2020 ◽  
Vol 0 (0) ◽  
Author(s):  
Awadhesh Kumar Poddar ◽  
Divyanshi Sharma
Keyword(s):  
Perturbation Theory ◽  
Rigid Body ◽  
Coordinate System ◽  
Periodic Orbits ◽  
Restricted Problem ◽  
Equations Of Motion ◽  
Three Dimensional ◽  
General Perturbation ◽  
Triaxial Rigid Body ◽  
Three Dimensional Coordinate

AbstractIn this paper, we have studied the equations of motion for the problem, which are regularised in the neighbourhood of one of the finite masses and the existence of periodic orbits in a three-dimensional coordinate system when μ = 0. Finally, it establishes the canonical set (l, L, g, G, h, H) and forms the basic general perturbation theory for the problem.

Equations of motion of the restricted problem of three bodies with variable mass

1983 ◽  
Vol 30 (3) ◽  
pp. 323-328 ◽  
Author(s):  
A. K. Shrivastava ◽  
Bhola Ishwar
Keyword(s):  
Restricted Problem ◽  
Equations Of Motion ◽  
Variable Mass

Equations of Motion of the Elliptical Restricted Problem of Three Bodies with Variable Masses

2001 ◽  
Vol 121 (1) ◽  
pp. 580-583 ◽  
Author(s):  
Subodh Kumar Jha ◽  
A. K. Shrivastava
Keyword(s):  
Restricted Problem ◽  
Equations Of Motion

scholarly journals Motion near The Unit Circle in The Three-Body Problem

1999 ◽  
Vol 172 ◽  
pp. 281-290
Author(s):  
Roger A. Broucke
Keyword(s):  
Linear System ◽  
Unit Circle ◽  
Restricted Problem ◽  
Body Problem ◽  
Equations Of Motion ◽  
Original System ◽  
Polar Coordinates ◽  
Three Body Problem ◽  
Simplified Models ◽  
Three Body

Many of the important applications of the circular planar restricted problem of three bodies involve motion in the vicinity of the unit circle, (as defined in canonical units). It is then of interest to develop simplified models which are valid in this region. These models preserve the gross characteristics of the original system but they possess simpler equations of motion.We will also show that several simplified models can be seen as a perturbation of a very well known simple linear system: the Clohessy-Wiltshire equations used by NASA in all their rendezvous operations. These are actually very close to the well-known Hill problem. We will thus consider the Restricted problem as a perturbed Hill or Clohessy-Wiltshire problem. We also introduce the Clohessy-Wiltshire Lagrangian in polar coordinates.

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