Fuel Optimal, Finite Thrust Guidance Methods to Circumnavigate with Lighting Constraints

Document Type

Conference Proceeding

Publication Date

9-14-2017

Abstract

This paper details improvements made to the authors most recent work to find fuel optimal, finite-thrust guidance to inject an inspector satellite into a prescribed natural motion circumnavigation (NMC) orbit about a resident space object (RSO) in geosynchronous orbit (GEO). Better initial guess methodologies are developed for the low-fidelity model nonlinear programming problem (NLP) solver to include using Clohessy Wiltshire (CW) targeting, a modified particle swarm optimization (PSO), and MATLABs genetic algorithm(GA). These initial guess solutions may then be fed into the NLP solver as an initial guess, where a different NLP solver, IPOPT, is used. Celestial lighting constraints are taken into account in addition to the sunlight constraint, ensuring that the resulting NMC also adheres to Moon and Earth lighting constraints. The guidance is initially calculated given a fixed final time, and then solutions are also calculated for fixed final times before and after the original fixed final time, allowing mission planners to choose the lowest-cost solution in the resulting range which satisfies all constraints. The developed algorithms provide computationally fast and highly reliable methods for determining fuel optimal guidance for NMC injections while also adhering to multiple lighting constraints. Abstract © AMOS.

Comments

Copyright © 2017 Advanced Maui Optical and Space Surveillance Technologies Conference (AMOS)

The full paper is hosted at the conference publisher's archive using the "Link to Full Text" on this page, and is free to download. All other rights reserved.

Co-author E. Prince was an AFIT PhD student at the time of this conference. (AFIT-ENY-DS-18-S-071, September 2018)

Source Publication

Advanced Maui Optical and Space Surveillance Technologies (AMOS), 2017

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