On The Optimal Spacecraft Fuel Consumption in Low Earth Orbit
نویسندگان
چکیده
The optimization problem for a 6DOF satellite equipped with constant specific impulse thrusters is addressed in terms of fuel consumption. The vehicle is assumed to move in Low Earth Orbit: the Keplerian motion around the Earth is perturbed both by the molecular air impingement (aerodynamic drag) and by the gravitational field disturbance known as J2 effect. Further results are achieved by simplifying the environmental model and by assuming that the spacecraft is modeled as a point mass.
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