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Refining Lucy Mission Delta-V During Spacecraft Design Using Trajectory Optimization Within High-Fidelity Monte Carlo Maneuver AnalysisRecent advances linking medium-fidelity trajectory optimization and high-fidelity trajectory propagation/maneuver design software with Monte Carlo maneuver analysis and parallel processing enabled realistic statistical delta-V estimation well before launch. Completing this high-confidence, refined statistical maneuver analysis early enabled release of excess delta-V margin for increased dry mass margin for the Lucy Jupiter Trojan flyby mission. By 3.3 years before launch, 16 of 34 TCMs had 1000 re-optimized trajectory design samples, yielding tens of m/s lower 99%-probability delta-V versus targeting maneuvers to one optimal trajectory. One year later, 1000 re-optimized samples of all deterministic maneuvers and subsequent flybys further lowered estimated delta-V.
Document ID
20190029152
Document Type
Conference Paper
Authors
Mcadams, James V. (KinetX Aerospace, Inc Simi Valley, CA, United States)
Knittel, Jeremy M. (KinetX Aerospace, Inc Simi Valley, CA, United States)
Williams, Kenneth E. (KinetX Aerospace, Inc Simi Valley, CA, United States)
Englander, Jacob A. (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Ellison, Donald H. (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Stanbridge, Dale R. (KinetX Aerospace, Inc Simi Valley, CA, United States)
Sutter, Brian (Lockheed Martin Space Systems Co. Denver, CO, United States)
Berry, Kevin (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Date Acquired
August 19, 2019
Publication Date
August 11, 2019
Subject Category
Astrodynamics
Report/Patent Number
GSFC-E-DAA-TN71229
Meeting Information
2019 AAS/AIAA Astrodynamics Specialist Conference(Portland, ME)
Funding Number(s)
CONTRACT_GRANT: NNG13FC02C
Distribution Limits
Public
Copyright
Use by or on behalf of the US Gov. Permitted.
Technical Review
Single Expert
Keywords
Trojan
Lucy

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