A minimum propellant solution to an orbit-to-orbit transfer using a low thrust propulsion system

Details A minimum propellant solution to an orbit-to-orbit transfer using a low thrust propulsion system A minimum propellant solution to an orbit-to-orbit transfer using a low thrust propulsion system

Oct 1991

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1991asee.nasar....c&link_type=abstract

In its Research Reports: 1991 NASA/ASEE Summer Faculty Fellowship Program 4 p (SEE N92-15850 06-80)

Physics

Algorithms, Fuel Consumption, Low Thrust Propulsion, Nuclear Electric Propulsion, Solar Electric Propulsion, Spacecraft Propulsion, Spacecraft Trajectories, Trajectory Optimization, Transfer Orbits, Hamiltonian Functions, Mars (Planet), Orbital Maneuvering Vehicles, Runge-Kutta Method, Space Exploration

Scientific paper

The Space Exploration Initiative is considering the use of low thrust (nuclear electric, solar electric) and intermediate thrust (nuclear thermal) propulsion systems for transfer to Mars and back. Due to the duration of such a mission, a low thrust minimum-fuel solution is of interest; a savings of fuel can be substantial if the propulsion system is allowed to be turned off and back on. This switching of the propulsion system helps distinguish the minimal-fuel problem from the well-known minimum-time problem. Optimal orbit transfers are also of interest to the development of a guidance system for orbital maneuvering vehicles which will be needed, for example, to deliver cargoes to the Space Station Freedom. The problem of optimizing trajectories for an orbit-to-orbit transfer with minimum-fuel expenditure using a low thrust propulsion system is addressed.

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