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Simulation-Based Analysis and Prediction of Thrust Vector Servoelastic CouplingA method of analysis and prediction of servoelastic coupling in launch vehicles is presented, surveying the discovery and subsequent resolution of a predicted servoelastic resonance phenomenon affecting the NASA Space Launch System launch vehicle at specific flight conditions. A physics-based linearized multibody mechanization of the governing equations is combined with first principles analysis to demonstrate that antisymmetric bending of the solid rocket motors leads to a reduction of equivalent viscous modal damping through coupling with the thrust vector control actuators. The sensitivity to parameters and the effects of the resonance phenomenon on flight control performance and stability are confirmed through extensive simulation verification in the time and frequency domain. A novel enhancement in model fidelity that accounts for Coriolis effects of fluid flow on bending within the solid rocket motor case and nozzle is shown to add sufficient damping to reduce the risk of adverse control-structure interaction.
Document ID
20230009355
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Authors
Jeb S Orr
(Jacobs (United States) Dallas, Texas, United States)
John H Wall
(Jacobs (United States) Dallas, Texas, United States)
Timothy M Barrows
(Jacobs (United States) Dallas, Texas, United States)
Date Acquired
June 22, 2023
Publication Date
January 30, 2020
Subject Category
Spacecraft Propulsion and Power
Report/Patent Number
M20-7916
Meeting Information
Meeting: 43rd Annual American Astronautical Society (AAS) Guidance and Control (GN&C) Conference
Location: Breckenridge, CO
Country: US
Start Date: January 30, 2020
End Date: February 5, 2020
Sponsors: American Astronautical Society
Funding Number(s)
CONTRACT_GRANT: 80MSFC18C0011
Distribution Limits
Public
Copyright
Public Use Permitted.
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