Analysis of Various Two Synodic Period Earth-Mars Cycler Trajectories

Byrnes, Dennis V.; McConaghy, T. Troy; Longuski, James M.

doi:10.2514/6.2002-4423

Cited by 24 publications

(8 citation statements)

References 2 publications

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“…9−11 The existence of the Aldrin cycler was verified by Byrnes et al, 12 and the Aldrin cycler was compared to the VISIT cyclers by Friedlander et al 13 In 2002, McConaghy et al 14 showed that the Aldrin cycler and the VISIT cyclers are special cases in a larger family of cyclers. Several new cyclers were also identified by Byrnes et al, 15 Chen et al, 16−18 McConaghy et al, 19,20 Rauwolf et al, 21 and Russell and Ocampo. 22 −24 Among the recently discovered cyclers, one is particularly noteworthy.…”

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confidence: 81%

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Notable Two-Synodic-Period Earth-Mars Cycler

McConaghy

Landau

Yam

et al. 2006

Journal of Spacecraft and Rockets

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Earth-Mars cycler trajectories (cyclers) could play an important role in a future human transportation system to Mars. A particular cycler that repeats every two synodic periods and has one intermediate Earth encounter is very promising. In a circular-coplanar model it requires no propulsive maneuvers, has 153-day transfer times between Earth and Mars, and has arrival V ∞ magnitudes of 4.7 km/s at Earth and 5.0 km/s at Mars. A method to find an analog cycler in a more realistic model (i.e., using an accurate ephemeris for the states of Earth and Mars) is described. Two cost metrics are considered: total cycler ΔV and total cycler ΔV plus total taxi ΔV. Numerical solutions are presented for both metrics. The total required ΔV is very small, though not zero. If the Earth-Mars and Mars-Earth transit times are constrained, then the characteristics of the optimal cycler trajectory change. Tradeoffs between maximum transit time and other mission characteristics are analyzed for all possible launch periods. Nomenclature a = orbital elements vector g = vector of V ∞ constraints, km/s h = flyby altitude, km h = vector of flyby altitude constraints, km N = number of intermediate Earth flybys P = primer vector R = position vector of the cycler vehicle, AU S = Earth-Mars synodic period, year T = time for orbits of Earth and Mars to repeat inertially, year t = time since launch, year V ∞ = hyperbolic excess speed, km/s V = magnitude of change in velocity, km/s τ = duration of leg 1, 2.8276 years Subscripts i = Earth encounter index in = incoming out = outgoing

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confidence: 81%

“…14). It is similar to the "case 3" cycler of Byrnes et al 15 Using the cycler nomenclature proposed in Ref. 25, it has the cycler label "2g(2.8276, 658 • , U )g(1.4580, 525 • , L)."…”

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confidence: 96%

Notable Two-Synodic-Period Earth-Mars Cycler

McConaghy

Landau

Yam

et al. 2006

Journal of Spacecraft and Rockets

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“…Of course, the same approach could be used if the bodies under investigation were different from Earth and Moon (Byrnes et al, 2002).…”

Section: Introductionmentioning

confidence: 97%

Low-thrust transfer to Backflip orbits

Pergola

2010

Advances in Space Research

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“…6,8,9,12 In this study, we seek solutions in a circular-coplanar model only and refer to them as idealized solutions. It is hoped that subsequent studies will find the analogous real-world solutions based on the initial guesses from the simple model solutions.…”

Section: Introductionmentioning

confidence: 99%

Global Search for Idealized Free-Return Earth-Mars Cyclers

Russell

Ocampo

2005

Journal of Guidance, Control, and Dynamics

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A new technique is developed to globally identify and optimize all useful idealized Earth-Mars cyclers constructed with Earth-Earth free returns patched by gravity-assisted flybys. Previous techniques that use solutions of the multiple-revolution Lambert problem are expanded. Using combinatorics, the entire solution space is investigated for combinations of generic, half-revolution, and full-revolution free-return transfers for cyclers with periods up to three synodic periods. All three types of free returns are generalized to include the possibility for multiple revolutions. Multiple options for the short Earth-Mars and Mars-Earth legs that characterize the cyclers are included. The generalized technique requires the solutions to hundreds of thousands of minimax optimization problems and results in 142 previously undocumented ballistic cyclers. In addition, the global search verifies and encompasses results from several earlier studies that looked at a variety of subsets of the current solution space. The final list is exhaustive for the defined class of cyclers and is an excellent resource for future researchers that seek cyclers in a more realistic solar system.

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Analysis of Various Two Synodic Period Earth-Mars Cycler Trajectories

Cited by 24 publications

References 2 publications

Notable Two-Synodic-Period Earth-Mars Cycler

Notable Two-Synodic-Period Earth-Mars Cycler

Low-thrust transfer to Backflip orbits

Global Search for Idealized Free-Return Earth-Mars Cyclers

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