ANALYSIS OF IDEAL MANEUVERS FOR MISSION EXTENSION VEHICLE
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Authors
Mathies, Max S.
Subjects
orbital mechanics
GPOPS
proximity maneuvers
space flight
keplerian two body problem
circular orbit
mission extension vehicle
orbiting spacecraft
geosynchronous orbit
circular orbit
restricted kepler problem
Hill-Clohessy-Wiltshire
HCW
chief
deputy
linearized equations
optimization
traveling salesman
vehicle routing
TSP
GPOPS
proximity maneuvers
space flight
keplerian two body problem
circular orbit
mission extension vehicle
orbiting spacecraft
geosynchronous orbit
circular orbit
restricted kepler problem
Hill-Clohessy-Wiltshire
HCW
chief
deputy
linearized equations
optimization
traveling salesman
vehicle routing
TSP
Advisors
Romano, Marcello
Hudson, Jennifer
Date of Issue
2022-12
Date
Publisher
Monterey, CA; Naval Postgraduate School
Language
Abstract
Finding optimal maneuvers between spacecraft is computationally demanding. Targeting many spacecraft successively requires more computational power than commercially available. This thesis tested algorithms looking to reduce this computational burden. Algorithms claiming optimal two-impulse rendezvous solutions between any two arbitrary orbits were coded and compared through minimum delta-vs (fuel) and computational times. Orbit characteristics were varied across a multitude of scenarios to represent many possible applications. Assorted considerations were discussed, which provided a framework for designing multi-client on-orbit servicing missions.
Type
Thesis
Description
Series/Report No
Department
Mechanical and Aerospace Engineering (MAE)
Organization
Identifiers
NPS Report Number
Sponsors
Funder
Format
Citation
Distribution Statement
Approved for public release. Distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.