Deployable Engine Air-Brake for Drag Management Applications

Award Information
National Aeronautics and Space Administration
Award Year:
Phase I
Agency Tracking Number:
Solicitation Year:
Solicitation Topic Code:
Solicitation Number:
Small Business Information
ATA Engineering, Inc.
11995 El Camino Real, Suite 200, San Diego, CA, -
Hubzone Owned:
Minority Owned:
Woman Owned:
Principal Investigator:
Parthiv Shah
Principal Investigator
(858) 480-2101
Business Contact:
Ronan Cunningham
Business Official
(858) 480-2000
Research Institution:

ATA Engineering, Inc., proposes an SBIR program to demonstrate an innovative engine air-brake (EAB) technology that uses a deployable swirl vane mechanism to switch the operation of a turbofan engine nozzle from a conventional to a "drag management" mode. Such "drag on demand" enables operational benefits such as slower, steeper, and/or aeroacoustically cleaner flight on approach, addressing NASA's need for active and passive control of aeroacoustic noise sources for conventional and advanced aircraft configurations.The proposing team recently completed a Phase I/II SBIR program on the development of an EAB for quiet drag applications. This program began with design of aerodynamic concepts and progressed to fabrication and testing of several prototypes in NASA Glenn's Aero Acoustic Propulsion Laboratory. Results suggested that an appropriately designed EAB could enable a fixed-speed, steep approach trajectory from a baseline 3.2 to 4.4 degree glideslope for a 737-800-class aircraft, with 3.1 dB peak tone-corrected perceived noise (PNLT) reduction and 1.8 dB effective perceived noise level (EPNL) reduction. The previous effort culminated in a conceptual design of a bypass nozzle mechanism that stows in an aerodynamically "invisible" manner in the nozzle casing during conventional operation and introduces deployable vanes in a drag management maneuver.Current technology readiness level (TRL) is 3 to 4, and the proposed SBIR program aims to advance TRL to 5 to 6 by demonstrating a prototype that switches between stowed and deployed mode during operation. The technical objectives are to: (1) evaluate and select a candidate nozzle or engine as a demonstrator, (2) develop a preliminary aerodynamic and mechanical design of an integrated mechanism, and (3) define a validation plan that can be executed in Phase II. The final deliverable will be a written report to NASA presenting the findings and designs and defining the path forward for Phase II activities.

* information listed above is at the time of submission.

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