Propulsion Test Support Analysis with GPU Computing

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX12CF59P
Agency Tracking Number: 114157
Amount: $124,968.00
Phase: Phase I
Program: SBIR
Awards Year: 2012
Solicitation Year: 2011
Solicitation Topic Code: O2.05
Solicitation Number: N/A
Small Business Information
PA, Pipersville, PA, 18947-1020
DUNS: 929950012
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Vineet Ahuja
 Principal Investigator
 (215) 766-1520
 vineet@craft-tech.com
Business Contact
 Katherine Young
Title: Business Official
Phone: (215) 766-1520
Email: youngk@craft-tech.com
Research Institution
 Stub
Abstract
The design, development and staging of tests to certify liquid rocket engines usually require high-fidelity structural, fluid and thermal support analysis. These analyses are crucial to a successful engine test program since pressurization requirements, heat loads, cooling requirements and structural stresses are evaluated. Furthermore, these analyses are utilized to detect anomalies, unsteady pressure pulsations, structural vibrations, resonant modes and unexpected plume impingement zones that may be hazardous to the test stand structure and/or the test article. Such high-fidelity analyses have traditionally been performed on PC-cluster type computational platforms spanning over days/weeks given the complexity of the flowpath and flow regimes typically involved in the testing of liquid rocket engines. In this proposal we exploit the data parallelism of the computational algorithms involved to significantly enhance performance on low-cost high-speed GPU enabled hardware. Such a transition to GPU-based hardware will result in a paradigm shift for compute-intensive propulsion system applications from expensive CPU dominated PC-cluster architectures to economical workstation styled hybrid GPU-CPU systems, while resulting in dramatic decreases in turnaround times.

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

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