Graphical Method for Gravity-Assist Trajectory Design

Strange, Nathan; Longuski, James M.

doi:10.2514/2.3800

Cited by 134 publications

(37 citation statements)

References 9 publications

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“…Other methods of space maneuvers use low thrust maneuvers (Casalino et al 1999;Fernandes and Carvalho 2008;Fernandes 2009;Gomes and Prado 2012). Alternative solutions use natural forces to maneuver a spacecraft, like in Broucke (1988), D'Amario et al (1982, Farquhar et al (1985), Felipe and Prado (1999), Strange and Longuski (2002), Prado (2003), Formiga and Prado (2014).…”

Section: Introductionmentioning

confidence: 97%

Studying the lifetime of orbits around Moons in elliptic motion

Gomes

Domingos

2015

Comp. Appl. Math.

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The main goal of the present paper is to study the lifetime of orbits around moons that are in elliptic motion around their parent planet. The lifetime of the orbits is defined as the time the orbit stays in orbit around the moon without colliding with its surface. The mathematical model used to solve this problem is the second order expansion of the potential of the disturbing planet, assumed to be in an elliptical orbit. The results are presented in maps showing the lifetime of the orbit as a function of its initial inclination and eccentricity. The only perturbation acting on the orbit of the spacecraft is assumed to be the gravity of the planet, so the problem is solved by studying the orbital evolution of the spacecraft perturbed by a third body in an elliptical orbit. The region of inclination above the critical value of the third-body perturbation (around 63 • ) is studied, since below that value the orbits survive for a long time. The influence of the eccentricity of the primaries is also investigated, assuming a hypothetical system that has the same mass parameter and sizes of the Earth-Moon system, but the eccentricity can be in the range 0.0-0.2.

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Section: Introductionmentioning

confidence: 97%

Studying the lifetime of orbits around Moons in elliptic motion

Gomes

Domingos

2015

Comp. Appl. Math.

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“…Sims et al [45,46] analyzed the orbit features of planetary swingbys with deep space orbit maneuvers. Strange et al [47] proposed analyzing the energy changes of spacecraft to identify viable swingby sequences.…”

Section: Design Of Planetary Swingby Orbitmentioning

confidence: 99%

A survey on orbital dynamics and navigation of asteroid missions

Baoyin

2014

Acta Mech Sin

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Asteroid exploration is currently one of the most concerned topics among international space agencies. Orbital dynamics and navigation are obviously crucial for asteroid exploration. This paper aims to give a brief review on the dynamics, control and navigation of asteroid reconnaissance orbits, including the heliocentric transfer orbit and near asteroid orbit. The developments in optimization techniques of the transfer segment are discussed in detail. We surveyed global researches in this field and made comments on several important progresses. The final section proposed a prospective of future studies with emphasis on the key techniques of these issues in the asteroid exploration missions.

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“…Many authors have addressed ballistic patched conics tour design [9,13,18,19,32,33], but few have presented systematic algorithms for representing the results in nbody ephemeris models. Typically, the transition to the full ephemeris model is made in a single leap, and can stress even the best optimization algorithms tackling the simplest of problems.…”

Section: Introductionmentioning

confidence: 99%

A Continuation Method for Converting Trajectories from Patched Conics to Full Gravity Models

Bradley

Russell

2014

J of Astronaut Sci

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A method is introduced to transition space trajectories from low fidelity patched conics models to full-ephemeris n-body dynamics. The algorithm incorporates a continuation method that progressively re-converges solution trajectories in systems with incremental changes in the dynamics. Continuation is accomplished through the variation of a control parameter, which is tied to body ephemeris locations and masses, minimum flyby altitudes, and sphere of influence sizes. The intermediate models provide a continuous and differentiable path between solutions in the simplified and n-body dynamics, and the boundary values of the control parameter replicate the patched conics and full-ephemeris models exactly. Each successive step preserves the qualitative properties of the initial guess by successively altering flyby states and body masses. A similar approach to this methodology may be taken with any simplified starting guess, such as a restricted three-body model. Trajectories computed using the patched conics conversion method presented here may include gravity assists and rendezvous with any number of target bodies, so the method is ideal for constructing interplanetary or intermoon tour missions, and is amenable to patching shorter segments together to form longer tours.

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Graphical Method for Gravity-Assist Trajectory Design

Cited by 134 publications

References 9 publications

Studying the lifetime of orbits around Moons in elliptic motion

Studying the lifetime of orbits around Moons in elliptic motion

A survey on orbital dynamics and navigation of asteroid missions

A Continuation Method for Converting Trajectories from Patched Conics to Full Gravity Models

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