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Application of GPS to Enable Launch Vehicle Upper Stage Heliocentric DisposalTo properly dispose of the upper stage of the Space Launch System, the vehicle must perform a burn in Earth orbit to perform a close flyby of the Lunar surface to gain adequate energy to enter into heliocentric space. This architecture was selected to meet NASA requirements to limit orbital debris in the Earth-Moon system. The choice of a flyby for heliocentric disposal was driven by mission and vehicle constraints. This paper describes the SLS mission for Exploration Mission -1, a high level overview of the Block 1 vehicle, and the various disposal options considered. The research focuses on this analysis in terms of the mission design and navigation problem, focusing on the vehicle-level requirements that enable a successful mission. An inertial-only system is shown to be insufficient for heliocentric flyby due to large inertial integration errors from launch through disposal maneuver while on a trans-lunar trajectory. The various options for aiding the navigation system are presented and details are provided on the use of GPS to bound the state errors in orbit to improve the capability for stage disposal. The state estimation algorithm used is described as well as its capability in determination of the vehicle state at the start of the planned maneuver. This data, both dispersions on state and on errors, is then used to develop orbital targets to use for meeting the required Lunar flyby for entering onto a heliocentric trajectory. The effect of guidance and navigation errors on this capability is described as well as the identified constraints for achieving the disposal requirements. Additionally, discussion is provided on continued analysis and identification of system considerations that can drive the ability to integrate onto a vehicle intended for deep space.
Document ID
20170012384
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Authors
Anzalone, Evan J. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Oliver, T. Emerson (Dynamic Concepts, Inc. Huntsville, AL, United States)
Date Acquired
December 19, 2017
Publication Date
September 25, 2017
Subject Category
Launch Vehicles And Launch Operations
Spacecraft Design, Testing And Performance
Report/Patent Number
M17-6308
Meeting Information
Meeting: Institute of Navigation (ION) GNSS+ 2017
Location: Portland, OR
Country: United States
Start Date: September 25, 2017
End Date: September 29, 2017
Sponsors: Institute of Navigation
Distribution Limits
Public
Copyright
Public Use Permitted.

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