Date of Award

9-2025

Document Type

Thesis

Degree Name

Master of Science in Space Systems

Department

Department of Aeronautics and Astronautics

First Advisor

Rachel M. Derbis, PhD

Abstract

CubeSats have an inherent limitation on volume due to their small form factor. Naturally, this extends to the capacity of on-board ΔV, thus limiting the maneuverability of the satellites. This limited maneuverability makes it extremely important to be intentional when planning out mission trajectories. The cislunar region subjects these trajectories to the gravitational forces of both the Earth and the Moon, making it all the more necessary to deliberately plan out maneuvers. The Circular Restricted Three Body Problem (CR3BP) provides a simpler model for estimating the motion of spacecraft within the cislunar region, allowing for the gravitational forces to be used for advantage. This research provides a base mission plan for how to put two 6U CubeSats into an L2 southern halo orbit for the the specific use case of liaison navigation. Specifically, this research leverages an orbit’s inherent stability and associated stable manifolds to minimize the cost for transfers. For the trajectories analyzed, CubeSat 1 will require 1.7836 km/s of ΔV, and CubeSat 2 will require 2.5973 km/s. An additional 1.0368 km/s would be required for station-keeping over a 5 year mission lifetime.

AFIT Designator

AFIT-ENY-MS-25-S-012

Comments

An embargo was observed for posting this dissertation on AFIT Scholar.
Approved for Public Release, Distribution A: Distribution Unlimited. PA Case Number 88ABW-2025-0794

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