Fuel-optimal Lorentz-augmented Spacecraft Formations Using Novelty Minimum Sliding Mode Error Feedback Controller

Abstract

A dynamics model of satellite formation flying (SFF) is derived in an elliptical orbit with the existence of J2 perturbation and the Lorentz force. The Lorentz force is considered as the propellantless electromagnetic propulsion for orbital maneuvering and maintenance. However, the direction of Lorentz force is limited by the local magnetic field and the velocity of the spacecraft with respect to the local magnetic field, which is unable to provide the required control acceleration timely; therefore, it always works as an auxiliary strategy to reduce the fuel consumptions. Based on the above assumptions, the fuel-optimal control scheme is proposed for the SFF based on the minimum sliding mode error feedback controller (MSMEFC), which is implemented by using the thruster control and Lorentz force. Moreover, the optimal trajectories of the required specific charge of deputy Lorentz spacecraft and the thruster-generated control acceleration have been developed with details, respectively. Numerical examples are presented to demonstrate the efficacy of the proposed controller to maneuver and maintenance the SFF with the optimal fuel consumptions.