Global Optimization of Multi-Flyby Trajectories for Multi-Orbital-Plane Constellations Inspection

TL;DR

This paper presents a comprehensive global optimization framework for designing multi-flyby trajectories to efficiently inspect large satellite constellations across multiple orbital planes, reducing fuel use and operational costs.

Contribution

It introduces an innovative orbital-plane-based inspection strategy and a three-layer optimization framework that leverages orbital inclination and RAAN adjustments for efficient satellite constellation inspection.

Findings

Effective inspection of tens of thousands of satellites demonstrated.

Significant reduction in total velocity increment achieved.

Framework outperforms traditional rendezvous optimization methods.

Abstract

The rapid expansion of mega-constellations in low Earth orbits has posed significant challenges to space traffic management, necessitating periodic inspections of satellites to ensure the sustainability of the space environment when economically feasible. This study addresses the orbital design challenge associated with inspecting numerous satellites distributed across multiple orbital planes through flybys by proposing an innovative orbital-plane-based inspection strategy. The proposed methodology reformulates the multi-satellite flyby problem into a multi-rendezvous trajectory planning problem by proposing an analytical approach to determine a maneuver-free inspection orbit that enables flyby of all satellites within a specific orbital plane. Additionally, a three-layer global optimization framework is developed to tackle this problem. The first layer establishes an approximate cost evaluation model for orbital plane visitation sequences, utilizing a genetic algorithm to identify the optimal sequence from a vast array of candidate planes, thereby maximizing inspection targets while minimizing fuel consumption. The second layer constructs a mixed-integer programming model to locally refine the rendezvous epochs and orbital parameters of each inspection orbit to reduce the total velocity increment. The third layer accurately computes the optimal impulsive maneuvers and trajectories between inspection orbits. In contrast to traditional low-Earth orbit rendezvous optimization frameworks, the proposed framework fully leverages the adjustable freedom in inclination and right ascension of the ascending node (RAAN) of inspection orbits, significantly reducing the total velocity increment. Simulation results demonstrate that the proposed method can effectively address the trajectory optimization problem associated with constellation inspection for tens of thousands of satellites.