Fuel-Optimal Formation Reconfiguration by Means of Unidirectional Low-Thrust Propulsion System

TL;DR

This paper develops guidance and control strategies for autonomous, fuel-efficient orbit reconfiguration of satellite formations using a single low-thrust propulsion system, addressing practical operational constraints.

Contribution

It introduces guidance and control schemes for under-actuated satellite formation reconfiguration with a single low-thrust nozzle, emphasizing practicality and minimal computational load.

Findings

Effective guidance and control schemes for single-nozzle reconfiguration.

Ability to operate within operational constraints like eclipse and ground contact.

Support for future satellite mission requirements.

Abstract

The use of electric low-thrust propulsion systems for orbit maneuvers is becoming a popular choice among satellite manufacturers due to their inherent merits over their chemical counterparts. Many designers choose to incorporate multiple of such thrusters to insure omnidirectional orbit maneuverability, while others choose to equip their satellite with only one thruster nozzle, aiming to reduce the required power, weight, and size of the orbit control system. This paper proposes guidance and control schemes to address the problem of autonomous optimal relative orbit reconfiguration for a formation of two satellites, one of which utilizes a single low-thrust throttleable nozzle. Such under-actuated orbit control system requires the controlled spacecraft to constantly slew to direct the nozzle to the desired thrust direction. These redirection attitude maneuvers are treated within the guidance layer by accommodating recurrent no-thrust periods during which slew maneuvers take place. The control loop is then closed with an MPC-like scheme. The main motivation of this article is to support the future missions of LuxSpace's flagship satellite, Triton-X. Since the proposed guidance and control schemes are meant to answer realistic market needs, they are designed to have some specific qualities that makes them attractive from the practical point of view. Namely, they require minimal computational loads, besides being able to accommodate operational time constraints, e.g. no thrusting during eclipse or during ground contact, within the guidance layer.