A numerical study of powered Swing-Bys around the Moon

Ferreira, Alessandra F. S.; Prado, A. F. B. A.; Winter, O. C.

doi:10.1016/j.asr.2015.04.016

Cited by 24 publications

(22 citation statements)

References 50 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Simulations are made for two different systems of primaries, Earth-Moon and Sun-Jupiter, to show the importance of the mass parameter in those maneuvers. It should be emphasized, at this point, that a global optimization of the whole trajectory is a mandatory and important step in this type of problem but, as done in references [1,2,4], an analyses of the powered Swing-By part of the mission can give several results that are useful when making the global planning, as shown in the next parts of the present paper. It is even possible to compensate errors in the approach trajectory.…”

Section: Introductionmentioning

confidence: 90%

“…The powered Swing-By maneuver combines the pure gravity Swing-By with an impulse applied to the spacecraft near the close encounter. The literature [1,2] shows a comparison between two types of powered Swing-By: (i) a maneuver where the impulse is applied exactly during the passage of the spacecraft by the periapsis of its orbit around the celestial body; (ii) a maneuver where the impulse is applied after the spacecraft enters the sphere of influence [3] of the celestial body. This is done to verify the efficiency of both maneuvers, which means to find the best maneuver to be made.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

A numerical mapping of energy gains in a powered Swing-By maneuver

2017

View full text Add to dashboard Cite

The present paper studies the effects of a powered Swing-By maneuver, considering the particular and important situations where there are energy gains for the spacecraft. The objective is to map the energy variations obtained from this maneuver as a function of the three parameters that identify the pure gravity Swing-By with a fixed mass ratio (angle of approach, periapsis distance and velocity at periapsis) and the three parameters that define the impulsive maneuver (direction, magnitude and the point where the impulse is applied). The mathematical model used here is the version of the restricted three-body problem that includes the Lemaître regularization, to increase the accuracy of the numerical integrations. It is developed and implemented by an algorithm that obtains the energy variation of the spacecraft with respect to the largest primary of the system in a maneuver where the impulse is applied inside the sphere of influence of the secondary body, during the passage of the spacecraft. The point of application of the impulse is a free parameter, as well as the direction of the impulse. The results

show abstract

Section: Introductionmentioning

confidence: 90%

Section: Introductionmentioning

confidence: 99%

A numerical mapping of energy gains in a powered Swing-By maneuver

2017

View full text Add to dashboard Cite

show abstract

“…In a sequence, Casalino et al (1999a) expanded this analytical study to cover the situation where the impulse is applied in different points of the trajectory. There are several other works considering the study of the swing-by maneuver combined with an impulse in the spacecraft based on numerical integration (Prado 1997;Casalino et al 1999b;Santos et al 2008;Silva et al 2013;Ferreira et al 2015Ferreira et al , 2017aFerreira et al , 2017bFerreira et al , 2017cPiñeros and Prado 2017).…”

Section: Introductionmentioning

confidence: 99%

Analytical study of the swing-by maneuver in an elliptical system

Ferreira

Prado

Winter

et al. 2018

Astrophys Space Sci

View full text Add to dashboard Cite

The objective of the present paper is to derive a set of analytical equations that describe a swing-by maneuver realized in a system of primaries that are in elliptical orbits. The goal is to calculate the variations of energy, velocity and angular momentum as a function of the usual basic parameters that describe the swing-by maneuver, as done before for the case of circular orbits. In elliptical orbits the velocity of the secondary body is no longer constant, as in the circular case, but it varies with the position of the secondary body in its orbit. As a consequence, the variations of energy, velocity and angular momentum become functions of the magnitude and the angle between the velocity vector of the secondary body and the line connecting the primaries. The "patched-conics" approach is used to obtain these equations. The configurations that result in maximum gains and losses of energy for the spacecraft are shown next, and a comparison between the results obtained using the analytical equations and numerical simulations are made to validate the method developed here.

show abstract

“…Later, Prado (1996) expanded this study by analyzing the addition of the application of an impulse in the spacecraft, with variable magnitude and direction, at the instant of the closest encounter. Ferreira et al (2015) made a more complete analysis of this problem using numerical integrations. Making a more general study, Casalino et al (1999a) presented an analytical study for Swing-By maneuvers with an impulse applied at different positions of the orbit, not only in the periapsis.…”

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

View full text Add to dashboard Cite

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

show abstract

A numerical study of powered Swing-Bys around the Moon

Cited by 24 publications

References 50 publications

A numerical mapping of energy gains in a powered Swing-By maneuver

A numerical mapping of energy gains in a powered Swing-By maneuver

Analytical study of the swing-by maneuver in an elliptical system

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

Contact Info

Product

Resources

About