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(Reference retrieved automatically from Web of Science through information on FAPESP grant and its corresponding number as mentioned in the publication by the authors.)

Analytical study of the powered Swing-By maneuver for elliptical systems and analysis of its efficiency

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Ferreira, Alessandra F. S. [1, 2] ; Prado, Antonio F. B. A. [1] ; Winter, Othon C. [2] ; Santos, Denilson P. S. [3]
Total Authors: 4
[1] INPE, BR-12227010 Sao Jose Dos Campos, SP - Brazil
[2] Sao Paulo State Univ UNESP, Grp Dinam Orbital & Planetol, BR-12516410 Guaratingueta, SP - Brazil
[3] Sao Paulo State Univ UNESP, BR-13876750 Sao Joao Da Boa Vista, SP - Brazil
Total Affiliations: 3
Document type: Journal article
Source: ASTROPHYSICS AND SPACE SCIENCE; v. 363, n. 7 JUL 2018.
Web of Science Citations: 1

Analytical equations describing the velocity and energy variation of a spacecraft in a Powered Swing-By maneuver in an elliptic system are presented. The spacecraft motion is limited to the orbital plane of the primaries. In addition to gravity, the spacecraft suffers the effect of an impulsive maneuver applied when it passes by the periapsis of its orbit around the secondary body of the system. This impulsive maneuver is defined by its magnitude and the angle that defines the direction of the impulse with respect to the velocity of the spacecraft (). The maneuver occurs in a system of main bodies that are in elliptical orbits, where the velocity of the secondary body varies according to its position in the orbit following the rules of an elliptical orbit. The equations are dependent on this velocity. The study is done using the ``patched-conics approximation{''}, which is a method of simplifying the calculations of the trajectory of a spacecraft traveling around more than one celestial body. Solutions for the velocity and energy variations as a function of the parameters that define the maneuver are presented. An analysis of the efficiency of the powered Swing-By maneuver is also made, comparing it with the pure gravity Swing-by maneuver with the addition of an impulse applied outside the sphere of influence of the secondary body. After a general study, the techniques developed here are applied to the systems Sun-Mercury and Sun-Mars, which are real and important systems with large eccentricity. This problem is highly nonlinear and the dynamics very complex, but very reach in applications. (AU)

FAPESP's process: 16/14665-2 - Astrodynamics applied to space vehicles.
Grantee:Antônio Fernando Bertachini de Almeida Prado
Support type: Regular Research Grants
FAPESP's process: 17/04643-4 - Dynamics and control of space systems by tether
Grantee:Denilson Paulo Souza dos Santos
Support type: Regular Research Grants
FAPESP's process: 16/24561-0 - On the relevance of small bodies in orbital dynamics
Grantee:Othon Cabo Winter
Support type: Research Projects - Thematic Grants
FAPESP's process: 16/23542-1 - Swing-By maneuvers with use of Impulses and Cables in Three Dimensions
Grantee:Alessandra Ferraz da Silva Ferreira
Support type: Scholarships in Brazil - Post-Doctorate