A Scalable Gas-Particle Flow Simulation Tool for Lander Plume-Surface Interaction and Debris Prediction

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: 80NSSC20C0032
Agency Tracking Number: 186552
Amount: $749,955.00
Phase: Phase II
Program: STTR
Solicitation Topic Code: T9
Solicitation Number: STTR_18_P2
Timeline
Solicitation Year: 2018
Award Year: 2020
Award Start Date (Proposal Award Date): 2020-01-09
Award End Date (Contract End Date): 2022-01-08
Small Business Information
701 McMillian Way Northwest, Suite D, Huntsville, AL, 35806-2923
DUNS: 185169620
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Manuel Gale
 (256) 726-4860
 manuel.gale@cfdrc.com
Business Contact
 Silvia Harvey
Phone: (256) 726-4858
Email: proposals-contracts@cfdrc.com
Research Institution
 Mississippi State University
 Lee Boulevard
Mississippi State, MS, 00000-0000
 Federally funded R&D center (FFRDC)
Abstract
Plume-regolith interaction during propulsive landing results in (1) the liberation of dust/debris particles that may collide and strike the landing vehicle and surrounding assets obscuring ground observation for safe landing and (2) craters that are formed on the landing surface, posing additional challenges to vehicle stability and surface operations. The Gas-Granular Flow Solver (GGFS) had previously been developed for simulating the multi-phase gas-particle interaction and transport simulations for the complex regolith compositions found on Moon and Mars. Eulerian-Eulerian models are applied to model gas and particle phases as continuum fluids. This project is aimed at overcoming scalability and performance limitations encountered with the original GGFS implementation through migration of the GGFS simulation models to the highly scalable Loci computational framework. In Phase I, the GGFS Eulerian-Eulerian approach for modeling gas-granular flows was implemented in Loci and the anticipated performance enhancements clearly demonstrated. The prototype simulation tool has been successfully applied to the InSight landing reconstruction effort at NASA MSFC/ER42. Phase II enhancements will include: (1) Vehicle dynamics during propulsive descent and ascent using an overset/moving-mesh approach with 6-DOF motion, (2) multi-component gas and polydisperse granular mixture models for physically-consistent plume/surface interactions, (3) GPU-implementation and performance assessments, (4) verification and validation.

* Information listed above is at the time of submission. *

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