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Active Control of a Scramjet Engine

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA8650-16-C-2741
Agency Tracking Number: F15A-T19-0077
Amount: $749,990.00
Phase: Phase II
Program: STTR
Solicitation Topic Code: AF15-AT19
Solicitation Number: 2015.0
Solicitation Year: 2015
Award Year: 2016
Award Start Date (Proposal Award Date): 2016-09-07
Award End Date (Contract End Date): 2018-12-05
Small Business Information
75A Harbert Drive
Beavercreek, OH 45440
United States
DUNS: 079509319
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Mo Samimy
 (614) 292-5012
Business Contact
 Ryan Meritt
Phone: (937) 912-9438
Research Institution
 The Ohio State University
 Feiqian (Sunny) Zong
Office of Sponsored Programs 1960 Kenny Road
Columbus, OH 43210
United States

 (614) 247-6080
 Nonprofit College or University

Scramjet engines are designed to operate across a wide Mach number range and typically incorporate isolator sections to provide sufficient back-pressure margin and prevent unstart. As military requirements become increasingly demanding, an active, closed-loop control system is necessary to maintain engine stability and power output. During Phase I, key components of a scramjet control system were developed, integrated, and tested on a proof-of-concept platform. In Phase II, the cavity shock trap geometry will be further optimized using a computational approach and the results experimentally validated. In addition, its ability to withstand a transient increase in backpressure will be explored. The multi-faceted skin friction sensors developed in Phase I will be optimized and combined into a single, commercial-grade unit. High-enthalpy pressure transducers will also be developed and tested. Reduced Order Models (ROMs) will be constructed and incorporated into the control algorithm, enabling it to detect potential unstart conditions and preemptively avert unstart. To investigate potential opportunities in scramjet flame-holding capabilities and combustion efficiency control, the cavity mixing processes, particularly while under direct excitation of the shear layer instabilities, will be explored. Finally, the system capabilities will be demonstrated at the ARC and in a government scramjet test facility.

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

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