Flight-Capable Self-Starting Scramjet Inlets

Award Information
Agency:
Department of Defense
Branch
n/a
Amount:
$749,979.00
Award Year:
2011
Program:
SBIR
Phase:
Phase II
Contract:
FA8650-11-C-2179
Award Id:
n/a
Agency Tracking Number:
F093-182-0143
Solicitation Year:
2009
Solicitation Topic Code:
AF093-182
Solicitation Number:
2009.3
Small Business Information
714 E. Monument Ave, Suite 201, Dayton, OH, -
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
780026220
Principal Investigator:
LanceJacobsen
President
(937) 531-6678
lance.jacobsen@gohypersonic.com
Business Contact:
LanceJacobsen
President
(937) 531-6678
lance.jacobsen@gohypersonic.com
Research Institute:
Stub




Abstract
ABSTRACT: GoHypersonic Inc. is proud to present the following Phase II SBIR Proposal to the AFRL/RZA involving the development, fabrication, and testing of a high-performing flight-capable self-starting scramjet inlet. Under our Phase I SBIR work, we have developed and validated a self-starting inward-turning scramjet inlet concept and created a coupled CFD/thermal design and analysis capability. Our Phase II plan involves the design, fabrication, and testing of a large-scale flight-weight scramjet inlet 6ft in length. Due to the expected development and fabrication costs of the scramjet inlet, we are proposing structural and wind tunnel testing Program Options outside of the scope of the Main Program budget. To accomplish these Program Options, we have identified interest and potential external funding sources within the AFRL Air Vehicles Directorate and NASA Langley for respective structural and aerodynamic experimental validation programs. Details for these Options have also been included within the proposal to facilitate directorate and agency discussion and coordination once an award is made. BENEFIT: At the end of a successful Phase I and Phase II program, the GHI team will possess integrated aerodynamic, structural, and thermal design, optimization, and manufacturing capabilities for large scale hot-structure scramjet inlets. These capabilities will be directly extendible to include other major scramjet components such as combustors, nozzles, fuselages, and control surfaces. These tools will combine efficient CFD solvers, sensitivity solvers, grid and surface generators, thermal and structural solvers, and optimization algorithms into one very advanced high-fidelity design tool. In addition, the Phase I and Phase II program will generate a much broader understanding of the self-starting inlet technology and robust inlet operability, which we believe is crucial to the future of scramjet flight as a whole. Furthermore, the incorporation of high-temperature nickel-based and refractory material manufacturing techniques and processes into the design cycle will reduce both initial design costs and final production costs, and streamline the overall design-to-flight process from start to finish.

* information listed above is at the time of submission.

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