Nonlinear relative dynamics of Lorentz spacecraft about J2-perturbed orbit. (March 2015)

• Record Type: Journal Article
• Authors: Huang, Xu; Yan, Ye; Zhou, Yang; Zhang, Hua
• Is Part Of: Proceedings of the Institution of Mechanical Engineers. Volume 229:Number 3(2015:Mar.)
• Page Start: 467
• Page End: 478
• Publication Date: 2015-03
• Subjects: Relative motion -- Lorentz spacecraft -- J2 perturbation -- spacecraft hovering -- rendezvous -- trajectory optimization; Aeronautics -- Periodicals; Astronautics -- Periodicals; Airplanes -- Design and construction -- Periodicals; Aerospace industries -- Periodicals; 629.1
• DOI: 10.1177/0954410014537231
• Languages: English
• ISSNs: 0954-4100

Abstract

The Lorentz force acted on a charged spacecraft via interaction with planetary magnetic field provides new means of propellantless electromagnetic propulsion. Active modulation of the surface charge allows the spacecraft to perform orbital maneuvers. By assuming the Earth's magnetic field could be modeled as a tilted dipole that co-rotates with Earth, a nonlinear dynamical model describing the orbital motion of Lorentz spacecraft with respect to J 2 -perturbed orbit is developed using Lagrangian mechanics. Two potential applications of the proposed model, J 2 -perturbed Lorentz-augmented spacecraft hovering and Lorentz-propelled rendezvous, are considered in this paper. Fuel-optimal control strategies are designed for hovering, and optimal trajectory of the specific charge of Lorentz spacecraft for propellantless rendezvous that minimizes the consumption of control energy is also derived via Gauss pseudospectral method. To capture the interactive effect of J 2 perturbations and Lorentz force on relative motion, comparisons are made between results derived from J 2 -perturbed model and unperturbed model for both applications. Numerical simulations prove the validity of the proposed relative dynamical model and the applicability of Lorentz force in J 2 -perturbed spacecraft hovering and rendezvous. Comparisons show that J 2 perturbation should be considered when long-term hovering is necessary or more precise rendezvous trajectory is required, especially for low Earth orbit where J 2 perturbation is one of the most dominant perturbative forces.