Two Classes of Cycler Trajectories in the Earth-Moon System

Casoliva, Jordi; Mondelo, Josep–Maria; Villac, Benjamin; Mease, Kenneth D.; Barrabés, Esther; Ollé, Mercè

doi:10.2514/1.46856

Cited by 8 publications

(4 citation statements)

References 18 publications

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“…The algorithm functions sufficiently well with these assumptions, though a relatively simple improvement to the algorithm could include implementing a PC method for the initial state values at each homotopy level and/or dynamic correction of the step size. Similar continuation approaches are used in other works to determine families of trajectories [5,10,11,28,39], but are also used explicitly to transfer between dynamical frameworks [8,22,30,31].…”

Section: Continuation To N-body Dynamicsmentioning

confidence: 96%

“…These methods require evaluation of the Jacobian of the smooth solution curve in order to traverse the solution space to the final desired system. A more general alternative to a simplistic fixed-step approach is to utilize a predictor-corrector (PC) scheme (utilized in [10,11,17,23], and in a more basic formulation in [25]). PC methods involve altering initial parameter values at each increment in the continuation, and may also involve dynamic alteration of the step size.…”

Section: Continuation To N-body Dynamicsmentioning

confidence: 99%

“…Another application of continuation methods is to determine orbit families and solution bifurcations. Continuation methodology has been applied to computing families of orbits about Earth-Moon L 1 [5,28], finding periodic orbits and optimal spacecraft placements in the Earth-Moon system [11], computing Earth-Moon transfer families and cycler trajectories [10,39], determining families of optimal multi-burn general orbit transfers [12], and calculating launch vehicle thrust profiles [25].…”

Section: Introductionmentioning

confidence: 99%

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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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Section: Continuation To N-body Dynamicsmentioning

confidence: 96%

Section: Continuation To N-body Dynamicsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

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

Bradley

Russell

2014

J of Astronaut Sci

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“…In comparison, the design of cycler orbits between the Earth and the Moon is much more complicated because the gravitational attraction of the two bodies must be considered. 3,4) In Refs. 3) and 4), cycler orbits are found numerically since analytical solutions are no longer available in the three-body problem (3BP).…”

Section: Introductionmentioning

confidence: 99%

Design of Earth-Moon Cyclers Using Primer Vector Theory

Hayashida

Bando

Hokamoto

2016

AEROSPACE TECHNOLOGY JAPAN

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The purpose of this study is to design orbits for transporting passengers and cargo regularly from the Earth to the Moon and back. To accomplish this, so-called "cycler orbits" are used. A cycler orbit is an orbit circulating regularly between two astronomical bodies and can be achieved through gravity-assist swingbys. This study consists of two steps. The first step exploits the mechanics of the "double lunar swingby" to realize a cycler orbit without expending propellant. The second step employs the primer vector theory to design low-cost transfer orbits and calculates the minimum fuel for the mission. The proposed method of this study can realize an Earth-Moon transportation system which operates every two months with a significantly lower cost than the previous method.

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A Dynamical System Approach to Orbit Down-Selection of Earth-Moon Autonomous Navigation Constellations

Villac

Chow

et al. 2011

J of Astronaut Sci

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The article develops a method for the exploration of a concept of autonomous navigation constellations in the Earth-Moon system. This concept consists of using autonomous GPS-like beacons on three-body periodic orbits to provide navigation services to an end-user in the larger Earth-Moon neighborhood. The autonomy of the constellation spacecraft would be achieved using LiAISON navigation as introduced by Hill, Born, and Lo. The article focuses on the problem of orbit down-selection for such a concept, which is approached by formulating an optimization problem. The discussion of potential cost functions and the resulting simplifications of the problem are addressed. A continuation based method that leverages the structure of periodic orbits in the circular restricted three-body problem is then proposed to analyze the problem. The method allows notably for a succinct representation of the solution space as a one-dimensional graph that highlights local and global extrema of the optimization problem. Illustration of the method using a simplified down-selection metric is discussed to balance the strengths and limitations of the approach.

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Two Classes of Cycler Trajectories in the Earth-Moon System

Cited by 8 publications

References 18 publications

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

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

Design of Earth-Moon Cyclers Using Primer Vector Theory

A Dynamical System Approach to Orbit Down-Selection of Earth-Moon Autonomous Navigation Constellations

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