Contingency-Aware Station-Keeping Control of Halo Orbits

TL;DR

This paper introduces a convex optimization-based control algorithm for fuel-efficient, contingency-aware stationkeeping of spacecraft in halo orbits, ensuring safety and low delta-v in three-body systems.

Contribution

It presents a novel convex trajectory-optimization approach that incorporates safety constraints and contingency plans for halo orbit stationkeeping.

Findings

Demonstrates low total delta-v in simulations

Provides safe exit strategies during propulsion loss

Validates effectiveness in Earth-Moon and Saturn-Enceladus systems

Abstract

We present an algorithm to perform fuel-optimal stationkeeping for spacecraft in unstable halo orbits with additional constraints to ensure safety in the event of a control failure. We formulate a convex trajectory-optimization problem to generate impulsive spacecraft maneuvers to loosely track a halo orbit using a receding-horizon controller. Our solution also provides a safe exit strategy in the event that propulsion is lost at any point in the mission. We validate our algorithm in simulations of the three-body Earth-Moon and Saturn-Enceladus systems, demonstrating both low total delta-v and a safe contingency plan throughout the mission.