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Earth-Mars cycling spacecraft have been proposed as potentially beneficial to Mars exploration. There are many types of cyclers, but their common characteristic is that they have a heliocentric trajectory that brings them close to both Earth and Mars at regular intervals. As usually envisioned, a large cycler spacecraft would conast of most of the required mass (for example, for life support), and the crew would travel to and from both planet; in a smaller "taxi" vehicle. The taxi vehicle trajectories would necessarily be hyperbolic; such trajectories have not received as much attention as the cycler trajectories but, unless they can be flown with reasonable propellant consumption and safety, the cycler concept is not feasible. In this work, propellant-minimizing transfers are f >und for both impulsive and low-thrust hyperbolic rendezvous. A heuristic method, called particle swarm, is used fcr the global optimization. [ABSTRACT FROM AUTHOR]

The article discusses the use of microelectromechanical system to proposed the distribution of sensing nodes in heliocentric orbit, wherein it mentions the orbit evolution can be controlled through through modulation. It mentions the use of partial differential equations (PDEs), akin to fluid mechanics dealing with continuum flow, and ordinary differential equations (ODEs) to model orbit revolution in astrodynamics.