Interplanetary mission design with aero-assisted manoeuvres multi-objective evolutive optimization

Lavagna, Michèle; Povoleri, A.; Finzi, A. Ercoli

doi:10.1016/j.actaastro.2005.03.052

Cited by 13 publications

(9 citation statements)

References 14 publications

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“…This problem is related to the situations considered in the present research, because the atmosphere passage acts like an impulsive maneuver in some aspects. References on this topic are Lewis and McRonald (1992), Lohar et al (1994), Sims et al (1995), Lohar et al (1996), Bonfiglio et al (2000), Sims et al (2000), Trask and Coverstone (2004), Lavagna et al (2005) and Armellin et al (2007).…”

Section: Introductionmentioning

confidence: 99%

A numerical study of powered Swing-Bys around the Moon

Ferreira

Prado

Winter

2015

Advances in Space Research

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Section: Introductionmentioning

confidence: 99%

A numerical study of powered Swing-Bys around the Moon

Ferreira

Prado

Winter

2015

Advances in Space Research

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“…This maneuver can also contribute to the capture of spacecrafts by celestial bodies, like shown in Nock and Upholf (1979), Lynam et al (2011) and Brasil et al (2015). Some authors considered this maneuver combined with a passage of the spacecraft by the atmosphere of a planet, known as ''aero-gravity assisted maneuver'', as shown in Lewis and McRonald (1992), Sims et al (1995Sims et al ( , 2000, Lohar et al (1996), Bonfiglio et al (2000), Lavagna et al (2005), Armellin et al (2007) and Gomes et al (2015). A combination of low thrust and gravity assists are used in McConaghy et al (2003), Okutsu et al (2006) and Santos et al (2008).…”

Section: Introductionmentioning

confidence: 99%

Effects of the eccentricity of the primaries in powered Swing-By maneuvers

Ferreira

Prado

Winter

et al. 2017

Advances in Space Research

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The present paper studies the powered Swing-By maneuver when performed in an elliptical system of primaries. It means that there is a spacecraft travelling in a system governed by the gravity fields of two bodies that are in elliptical orbits around their center of mass. The paper particularly analyzes the effects of the parameters relative to the Swing-By (V inf À ; r p ; w), the orbit of the secondary body around the primary one (e; m) and the elements that specify the impulse applied (dV ; a) to the spacecraft. The impulse is applied when the spacecraft passes by the periapsis of its orbit around the body, where it performs the Swing-By, with different magnitudes and directions. The inclusion of the orbital eccentricity of the primaries in this problem makes it closer to reality, considering that there are many known systems with eccentricities different from zero. In particular, there are several moons in the Solar System which orbits are not circular, as well as some smaller bodies, like the dwarf planet Haumea and its moons, which have eccentricities of 0.25 or even larger. The behavior of the energy variation of the spacecraft is shown in details, as well as the cases where captures and collisions occur. The results show the conditions that optimize this maneuver, according to some given parameters, and how much can be obtained in terms of gains or losses of energy using the best conditions found by the algorithm developed here.

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“…Optimization techniques have also being used in the planar version of the problem (Lohar et al 1994) or in the three-dimensional case (Lohar 1996). Mission design using this concept and multi-objective evolutive optimization can be found in Lavagna et al (2005). An interesting analytical approach is used in Elices (1995), deriving equations to obtain the maximum effect of this close approach.…”

Section: Introductionmentioning

confidence: 99%

Atmospheric close approaches with the Earth considering drag and lift forces

et al. 2015

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A maneuver called "Aero-Gravity Assisted" is known in the literature to increase the energy gains given by a close approach between a spacecraft and a planet using the atmosphere of the planet. In a sequence of studies related to this problem, the present paper studies close approaches between a spacecraft and the Earth, in situations where the passage is close enough to the surface of the Earth such that the spacecraft crosses its atmosphere. The dynamical model considers the atmosphere of the Earth, in terms of drag and lift, the gravitational fields of the Earth and the Sun, assumed to be points of mass, and the spacecraft. The Earth and the Sun are assumed to be in circular coplanar orbits around their common center of mass. The equations of motion are the ones given by the circular planar restricted three-body problem with the addition of the forces generated by the atmospheric drag and lift. The primary objective is to map the variations of energy of the orbits of the spacecraft due to this close approach. The results show how the atmosphere affects the trajectory of the spacecraft, generating situations where the variation of energy changes sign with respect to the gravity part of the maneuver or where they have a zero net result, based in the equilibrium

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Interplanetary mission design with aero-assisted manoeuvres multi-objective evolutive optimization

Cited by 13 publications

References 14 publications

A numerical study of powered Swing-Bys around the Moon

A numerical study of powered Swing-Bys around the Moon

Effects of the eccentricity of the primaries in powered Swing-By maneuvers

Atmospheric close approaches with the Earth considering drag and lift forces

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