scholarly journals A SURVEY ON EXTENSIONS OF THE PURE GRAVITY SWING-BY MANEUVER

2021 ◽  
Vol 57 (2) ◽  
pp. 445-457
Author(s):  
A. F. S. Ferreira ◽  
R. V. de Moraes ◽  
A. F. B. A. Prado ◽  
O. C. Winter ◽  
V. M. Gomes
Keyword(s):  
Angular Momentum ◽  
Mathematical Models ◽  
Numerical Simulations ◽  
Body Problem ◽  
Restricted Three Body Problem ◽  
Three Body Problem ◽  
Pure Gravity ◽  
Celestial Bodies ◽  
Patched Conics ◽  
Three Body

The present paper surveys the more recent techniques related to the swingby maneuver, where a spacecraft changes its energy and angular momentum by passing close to celestial bodies. It is focused on the literature related to extensions of this maneuver, with emphasis in the powered version, where an impulse is applied to the spacecraft near the closest approach. Several mathematical models are considered, including the patched-conics approximation for analytical studies, and the restricted three-body problem for the numerical simulations. The main goal is to show the models and the main conclusions available in the literature for those maneuvers. Some key results are shown to discuss important aspects of this maneuver, including the analysis of the energy variation of the spacecraft, the behavior of the trajectories and other applications.

scholarly journals Studying Close Approaches for a Cloud of Particles Considering Atmospheric Drag

2013 ◽  
Vol 2013 ◽  
pp. 1-10 ◽  
Author(s):  
Vivian Martins Gomes ◽  
Jorge Formiga ◽  
Rodolpho Vilhena de Moraes
Keyword(s):  
Mathematical Model ◽  
Numerical Simulations ◽  
Body Problem ◽  
Equations Of Motion ◽  
Restricted Three Body Problem ◽  
The Sun ◽  
Atmospheric Drag ◽  
Three Body Problem ◽  
Three Body ◽  
The Mathematical Model

The present paper has the goal of studying close approaches between a planet and a group of particles. The mathematical model includes the presence of the atmosphere of the planet. This cloud is assumed to be created by the passage of the spacecraft in the atmosphere of the planet, which can cause the explosion of the spacecraft. The system is assumed to be formed by the Sun, the planet, and the spacecraft that explodes and becomes a cloud of particles. The Sun and the planet are assumed to be in circular orbits and the motion is planar. The equations of motion are the ones given by the circular planar restricted three-body problem combined with the forces given by the atmospheric drag. In the numerical simulations, the planet Jupiter is the celestial body used for the close approaches. The initial positions and velocities of the spacecraft and the particles are specified at the periapsis, because it is assumed that this is the point where the explosion occurs.

On the modified circular restricted three-body problem with variable mass

New Astronomy ◽  
2021 ◽  
Vol 84 ◽  
pp. 101510
Author(s):  
Md Sanam Suraj ◽  
Rajiv Aggarwal ◽  
Md Chand Asique ◽  
Amit Mittal
Keyword(s):  
Body Problem ◽  
Variable Mass ◽  
Restricted Three Body Problem ◽  
Three Body Problem ◽  
Three Body

scholarly journals GEOMETRY OF HOMOCLINIC CONNECTIONS IN A PLANAR CIRCULAR RESTRICTED THREE-BODY PROBLEM

2007 ◽  
Vol 17 (04) ◽  
pp. 1151-1169 ◽  
Author(s):  
MARIAN GIDEA ◽  
JOSEP J. MASDEMONT
Keyword(s):  
Symbolic Dynamics ◽  
Body Problem ◽  
Invariant Manifolds ◽  
Libration Point ◽  
Homoclinic Orbits ◽  
Restricted Three Body Problem ◽  
Three Body Problem ◽  
Lyapunov Orbits ◽  
Homoclinic Connections ◽  
Three Body

The stable and unstable invariant manifolds associated with Lyapunov orbits about the libration point L1between the primaries in the planar circular restricted three-body problem with equal masses are considered. The behavior of the intersections of these invariant manifolds for values of the energy between that of L1and the other collinear libration points L2, L3is studied using symbolic dynamics. Homoclinic orbits are classified according to the number of turns about the primaries.

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