Journal Article10.2514/1.1011
Systematic Method for Constructing Earth-Mars Cyclers Using Free-Return Trajectories
Ryan P. Russell,Cesar A. Ocampo +1 more
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TL;DR: Solutions from the multiple-revolution Lambert problem are utilized to find free-return Mars trajectories and find several known idealized cyclers, most of the orbits presented are previously undocumented.
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Abstract: A procedure for constructing idealized Earth-Mars cycler orbits in a simple solar system is presented. Solutions from the multiple-revolution Lambert problem are utilized to find free-return Mars trajectories. Multiple combinations of these generic return orbits are patched to sequences of full and half-revolution return orbits with Earth-generated gravity-assisted maneuvers. An algorithm is developed to find all useful combinations of the defined free returns that have a combined period of any integer multiple of the synodic period. Given a sequence of free returns, a procedure is then developed to minimize the maximum of all of the turning angles associated with the flybys necessary to maintain and reinitiate the cycler. The method identifies 24 ballistic cyclers with periods of two to four synodic periods, 92 ballistic cyclers with periods of five or six synodic periods, and hundreds of near-ballistic cyclers, where a ballistic cycler is defined to be one that requires no powered maneuvers to maintain and has realistic turning angles with respect to the surface of the Earth. These resulting orbits have diverse characteristics that could benefit a variety of potential missions. Although the method finds several known idealized cyclers, most of the orbits presented are previously undocumented.
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Base on Phobos — Much safer exploration of Mars without the need for humans on the surface of the planet
TL;DR: In this article , the authors discussed the challenges of colonizing Mars and proposed three different flight schemes for the most realistic one of them, and optimized the trajectory of flight to Phobos with starting since year 2020 for year 2030.
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Optimal Two-Impulse Rendezvous Using Multiple-Revolution Lambert Solutions
Haijun Shen,Panagiotis Tsiotras +1 more
TL;DR: In this paper, the minimum-V, e xed-time, two-impulse transfer problem between two e −ed points on two circular orbits is first solved by a simple transformation, and a solution procedure is proposed based on the study of an auxiliary transfer problem.
Cycler orbit between Earth and Mars
Abstract: A periodic orbit between Earth and Mars has been discovered that, after launch, permits a space vehicle to cycle back and forth between the planets with moderate maneuvers at irregular intervals. A Space Station placed in this cycler orbit could provide a safe haven from radiation and comfortable living quarters for astronauts en route to Earth or Mars. The orbit is largely maintained by gravity assist from Earth. Numerical results from multiconic optimization software are presented for a 15-year period from 1995 through 2010.
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A Class of Optimal Two-Impulse Rendezvous Using Multiple-Revolution Lambert Solutions
TL;DR: In this article, an algorithm based on the classical Lagrange formulation for an elliptic orbit is developed that determines all the trajectories for rendezvous with a target in the same circular orbit as the spacecraft.
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Geometric Analysis of Free-Return Trajectories Following a Gravity-Assisted Flyby
Ryan P. Russell,Cesar A. Ocampo +1 more
TL;DR: In this paper, the authors systematically identify all feasible trajectories following a gravity-assisted flyby that immediately return to the flyby body with no intermediate maneuvers, including even nπ, odd nπ and generic return orbits.
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Periodic orbits for interplanetary flight.
TL;DR: The possibility exists that a spacecraft can be placed on a free-fall trajectory that goes back and forth between Earth and Venus forever as discussed by the authors, and the trajectories have been found using patched-conic analysis.
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