NASA STTR 2018-I Solicitation

Proposal Summary


PROPOSAL NUMBER:
 18-1- T9.01-6232
SUBTOPIC TITLE:
 Lander Systems Technology
PROPOSAL TITLE:
 Prediction of Plume Induced Rock Fracture for Landers
SMALL BUSINESS CONCERN (SBC):
RESEARCH INSTITUTION (RI):
Name:   CFD Research Corporation
Name:   Los Alamos National Laboratory
Street:  701 McMillian Way Northwest, Suite D
Street:  P.O. Box 1663, Feynman Center for Innovation, MS C334
City:   Huntsville
City:   Los Alamos
State/Zip:  AL  35806-2923
State/Zip:   NM 87545 - 0001
Phone:  (256) 726-4800
Phone:   (505) 667-5324


Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)
Ranjan Mehta
rsm@cfdrc.com
701 McMillian Way Northwest, Suite D Huntsville, AL 35806 - 2923
(256) 726-4800

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)
Silvia Harvey
silvia.harvey@cfdrc.com
701 McMillian Way Northwest, Suite D Huntsville, AL 35806 - 2923
(256) 726-4858
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract

The landing surface damage and liberation of debris particles caused by rocket plume impingement flow during spacecraft propulsive landing on unprepared surfaces of Moon, Mars, and other celestial bodies poses a high risk for robotic and human exploration activities.  Simply determining whether the plume induced loads exceed the bedrock bearing capacity threshold is not sufficient. An integrated multi-physics simulation tool is required to capture and quantify the onset, progression and ultimate extent of the bedrock fracture processes and identify the dangers of the resulting debris transport and landing surface destruction. No such simulation capability exists to date. CFDRC has teamed with the Los Alamos National Laboratory (LANL) to propose the development of such a simulation tool that combines state-of-the-art computational fluid dynamics software for plume flowfield with a dynamic fracture mechanics structural analysis software of the rock material under plume impingement loads.  The Phase I will focus on demonstrating feasibility of the proposed approach with a TRL of 2 to 3.  In Phase II the models will be extended and validated to provide an accurate numerical approach for simulating plume induced rock fracture, debris transport and analysis tool, increasing the TRL by end of Phase II from 3 to 5. 

Potential NASA Applications

The proposed development will offer NASA currently non-existing simulations capabilities for propulsion integration effects assessment earlier during EDL&A concept development and systems integration trade-offs. The tools will enable definition of landing pad strength and maintenance/repair infrastructure required for sustainable outpost operation scenarios. Robotic exploration scenarios frequently involve site hopping of probes with repeated take-off and landing damage potential.

Potential Non-NASA Applications

Potential non-NASA applications include: a) Propulsive landing plume-surface interaction effects and debris damage assessment for commercial lander developers such as SpaceX’s planned Big Falcon Spaceship for Mars exploration and others planned by entities such as Blue Origin, b) Damage prediction and resulting debris predictions for military aircraft vertical take-off and landing, and c) Damage assessment and debris predictions for future military and commercial autonomous drones operations.


Form Generated on 05/25/2018 11:56:22