Aero-gravity assist maneuvers: controlled dynamics modeling and optimization

Armellín, Roberto; Lavagna, Michèle; Ercoli-Finzi, A.

doi:10.1007/978-1-4020-5325-2_23

Cited by 4 publications

(3 citation statements)

References 17 publications

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“…The nature of the interaction is irrelevant, as long as it is central and conservative. Evidently we are not considering for the moment variations of the manoeu- vre such as aero-gravity assisted slingshots 18 where at perigee the forces involved are neither conservative nor central. The particular value of Õ that corresponds to the theoretical maximum slingshot case is when Õ equals half the angle Ý o between v o ¹ u o and V cm , which means that u 1 and v 1 would both come out collinear to the CM velocity V cm .…”

Section: The Slingshot Manoeuvrementioning

confidence: 99%

Binary collisions and the slingshot effect

Silva¹,

Lemos²

2008

Celestial Mech Dyn Astr

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We derive the equations for the gravity assist manoeuvre in the general 2D case without the constraints of circular planetary orbits or widely different masses as assumed by Broucke (AIAA/AAS 1988) and obtain the slingshot conditions and maximum energy gain for arbitrary mass ratios of two colliding rigid bodies. Using the geometric view developed in an earlier paper by the authors (Rica da Silva, A., Lemos, J.P.S.: Am. J. Phys. 74, [584][585][586][587][588][589][590] 2006) the possible trajectories are computed for both attractive or repulsive interactions yielding a further insight on the slingshot mechanics and its parametrization. http:// centra.ist.utl.pt/amaro/Collisions/Collisions.html. The general slingshot manoeuvre for arbitrary masses is explained as a particular case of the possible outcomes of attractive or repulsive binary collisions, and the correlation between asymptotic information and orbital parameters is obtained in general.

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Section: The Slingshot Manoeuvrementioning

confidence: 99%

Binary collisions and the slingshot effect

Silva¹,

Lemos²

2008

Celestial Mech Dyn Astr

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“…In addition, an aerocapture maneuver can adjust the phase and flight velocity of an interplanetary probe to fly along an ideal trajectory. Such an aerocapture mode is called aerogravity assist (AGA) [17][18][19]. Note that in both cases, the target orbit is eventually reached after aerocapture through an intermediate transfer orbit, such as the stable manifold of a halo orbit or an interplanetary transfer orbit.…”

Section: Introductionmentioning

confidence: 99%

Rapid Construction of Aerocapture Attainability Sets Using Sequential Convex Programming

2022

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This paper proposes a novel method to efficiently construct the aerocapture attainability set based on convex optimization. Using dimensionality reduction, constructing the attainability set is equivalent to solving a set of discrete points on its boundary. As solving each of the boundary points is a typical nonlinear optimal control problem, a sequential convex programming method is adopted. The efficiency and accuracy of the proposed algorithm is demonstrated by high-fidelity numerical results. This is the first time that the configuration of the aerocapture attainability set is precisely described by the state variables at atmospheric exit. Since the quantification of the set is significant for assessing the feasibility of performing an aerocapture maneuver, the proposed method can be used as a reliable tool for systematic design for aerocapture mission.

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“…In particular, the use of "Aero-Gravity Assisted Maneuver" in Mars and/or Venus using higher values for the lift/drag ratio to go to more distant planets, in particular Pluto, or even the Sun, are considered in many publications (McRonald and Randolph 1992;Lewis and McRonald 1992;Bonfiglio et al 2000;Sims et al 1995Sims et al , 2000Lohar et al 1997;Randolph and McRonald 1992). The consideration of the shape and/or structure of the spacecraft is also studied (Armellin et al 2006(Armellin et al , 2007. 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).…”

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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Aero-gravity assist maneuvers: controlled dynamics modeling and optimization

Cited by 4 publications

References 17 publications

Binary collisions and the slingshot effect

Binary collisions and the slingshot effect

Rapid Construction of Aerocapture Attainability Sets Using Sequential Convex Programming

Atmospheric close approaches with the Earth considering drag and lift forces

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