What is it about?

Trajectory design for emerging propulsion technologies such as solar-electric propulsion is computationally intensive. This paper develops a quick preliminary design method for the purposes of estimating these trajectory costs. The developed model can be used for the computationally efficient initial design of lunar missions.

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Why is it important?

The developed method enables efficient low-thrust, low-energy trajectory design in cislunar space with a reasonable accuracy. It provides a way to bridge the gap between the computationally expensive yet accurate high-fidelity trajectory analysis methods and the quick yet less accurate low-fidelity trajectory analysis methods. The developed method improve the efficiency for large-scale trade space exploration and optimization for future complex space mission design.


This research was originally initiated as a component of a larger space logistics mission design effort, but since its result was very interesting, we decided to publish this as an independent paper with a focus on astrodynamics. We hope you find this article interesting, and, if you are interested, please also check out our follow-up space logistics mission design paper on the Journal of Spacecraft and Rockets (https://arc.aiaa.org/doi/10.2514/1.A34628).

Assistant Professor Koki Ho
Georgia Institute of Technology

Read the Original

This page is a summary of: Preliminary Design of Low-Energy, Low-Thrust Transfers to Halo Orbits Using Feedback Control, Journal of Guidance Control and Dynamics, February 2019, American Institute of Aeronautics and Astronautics (AIAA), DOI: 10.2514/1.g003759.
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