Studying the energy variation in the powered Swing-By in the Sun-Mercury system

Ferreira, Alessandra F. S.; Prado, A. F. B. A.; Winter, O. C.; Santos, Denílson Paulo Souza dos

doi:10.1088/1742-6596/911/1/012007

Cited by 2 publications

(2 citation statements)

References 11 publications

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“…Both of those planets have been considered many times for Swing-By maneuvers [24][25][26][27] and can benefit from the present computational study. In these cases, the effects of the maneuver are larger when we consider their eccentricities, as shown in [28] and [29].…”

Section: Introductionmentioning

confidence: 97%

A computational approach to the powered Swing-By in the elliptic restricted problem

Ferreira

Moraes

Prado

et al. 2021

J Braz. Soc. Mech. Sci. Eng.

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This work performs a computational investigation of the energy variations given by a powered Swing-By maneuver realized in an elliptical system. It extends previous works by giving the freedom to choose the location and the direction of the thrust vector, aspects that were not considered before in the literature. Those variations are obtained numerically as a function of the parameters related to the thrust (magnitude, direction and location of the application) and the orbital parameters of the primaries (eccentricity and true anomaly). The maneuver is realized around the smaller primary, and the energy variations are measured with respect to the main body of the system. The initial orbit of the space vehicle is defined by its periapsis distance, angle and approach velocity with respect to the smaller primary. The study is applied to a system composed of two primaries that are in elliptic orbits around the center of mass of the system. The eccentricity is varied as a free parameter, to measure its effects. The results show that the best maneuvers apply the thrust at a point inside the sphere of influence of the secondary body, but not in the periapsis of the orbit. The best direction of the thrust is not aligned with the motion of the space vehicle. The techniques studied here are applied in situations where it is desired to increase the energy of the space vehicle. Empirical equations are obtained for the energy variations, based on the simulations made in the present paper. The numerical approach makes the results more accurate and not limited to particular regions of the eccentricity.

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Section: Introductionmentioning

confidence: 97%

A computational approach to the powered Swing-By in the elliptic restricted problem

Ferreira

Moraes

Prado

et al. 2021

J Braz. Soc. Mech. Sci. Eng.

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“…An example of an even higher eccentric system in the Solar System is the dwarf planet Haumea, which has a moon with an eccentricity close to 0.25 (Sanchez et al 2016). A first study of maneuvers in eccentric systems is shown in Prado (1997), which studied the pure gravity Swing-By maneuver (without impulses) for the elliptic case and Ferreira et al (2017cFerreira et al ( , 2017a, which made a numerical study of the powered Swing-By maneuver, with the impulse applied at the periapsis of the orbit of the spacecraft around the secondary body of the system and in different directions, considering the two main bodies in elliptical orbits. An analysis of the effect of the eccentricity was presented in these papers, besides the study of the maximum gains and losses of energy obtained from the maneuver.…”

Section: Introductionmentioning

confidence: 99%

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

Ferreira

Prado

Winter

et al. 2018

Astrophys Space Sci

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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 δV and the angle that defines the direction of the impulse with respect to the velocity of the spacecraft (α). 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 maneu-B A.F.S. Ferreira

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Studying the energy variation in the powered Swing-By in the Sun-Mercury system

Cited by 2 publications

References 11 publications

A computational approach to the powered Swing-By in the elliptic restricted problem

A computational approach to the powered Swing-By in the elliptic restricted problem

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

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