Gravitational disturbances generated by the Sun, Phobos and Deimos in orbital maneuvers around Mars with automatic correction of the semi-major axis

17th Brazilian Colloquium on Orbital Dynamics

Rocco, E.M.^1

National Institute for Space Research - INPE, Space Mechanics and Control Division, São José dos Campos, SP, Brazil^1

关键词: Automatic corrections;    Disturbance effects;    Gravitational attraction;    Gravitational potential;    Lambert's problem;    Minimum fuel consumption;    Orbital maneuvers;    Propulsion system;   

Others  :  https://iopscience.iop.org/article/10.1088/1742-6596/641/1/012027/pdf
DOI  :  10.1088/1742-6596/641/1/012027

来源: IOP

【 摘 要 】

The objective of this work is to analyze orbital maneuvers of a spacecraft orbiting Mars, considering disturbance effects due to the gravitational attraction of the Sun, Phobos and Deimos, beyond the disturbances due to the gravitational potential of Mars. To simulate the trajectory, constructive aspects of the propulsion system were considered. Initially ideal thrusters, capable of applying infinite magnitude of the thrust, were used. Thus, impulsive optimal maneuvers were obtained by scanning the solutions of the Lambert's problem in order to select the maneuver of minimum fuel consumption. Due to the impossibility of applying an impulse, the orbital maneuver must be distributed in a propulsive arc around the position of the impulse given by the solution of the Lambert's problem. However the effect of the propulsive arc is not exactly equivalent to the application of an impulse due to the errors in magnitude and direction of applied thrust. Therefore, the influence of the thrusters' capacity in the trajectory was evaluated for a more realistic model instead of the ideal case represented by the impulsive approach. Beyond the evaluation of the deviation in the orbital path, was considered an automatic correction of the semi-major axis using continuous low thrust controlled in closed loop to minimize the error in the trajectory after the application of the main thrust.