Advanced Measurement Technology for Airframe Noise Source Identification

The Interdisciplinary Consulting Corporation (IC2), in partnership with AVEC, Inc., proposes to develop advanced phased-array and dynamic pressure sensing instrumentation and processing capabilities for airframe noise source identification. High channel-count, high-density, low cost-per-channel microphone arrays, and ultra-small, ultra-smooth sensing surface, low-cost, instrumentation-grade, model-embedded dynamic pressure sensors, both using microelectromechanical systems (MEMS) piezoelectric sensors with backside contacts and advanced packaging technology, will be combined with advanced array processing capabilities to create innovative airframe noise source identification capabilities. The goals of this research include: (1) developing high-fidelity phased arrays, with flexible mounting options including surface mounting, to avoid encumbrances typical when through-wall installations are required with existing commercial instrumentation products; (2) developing dynamic pressure sensors that can be embedded in model-scale parts, such as landing gear components, flaps, and slats, with ultra-smooth surface outcomes such that the instrumentation itself does not impact the fluctuating pressures that are being measured; and (3) developing advanced phased-array processing algorithms that combine propagating acoustic signals received at the array with localized fluctuating pressure signals measured at the model surfaces to directly correlate noise source generating regions with propagating acoustics. The Interdisciplinary Consulting Corporation (IC2), in partnership with AVEC, Inc., proposes to develop advanced phased-array and dynamic pressure sensing instrumentation and processing capabilities for airframe noise source identification. High channel-count, high-density, low cost-per-channel microphone arrays, and ultra-small, ultra-smooth sensing surface, low-cost, instrumentation-grade, model-embedded dynamic pressure sensors, both using microelectromechanical systems (MEMS) piezoelectric sensors with backside contacts and advanced packaging technology, will be combined with advanced array processing capabilities to create innovative airframe noise source identification capabilities.   This work is aimed at addressing the aerospace industry’s need for technically feasible and economically viable airframe noise source identification measurement capabilities that enable required noise diagnostic capabilities including connecting the root cause of the noise with the effect. Phase II objectives: Review sensor performance and array processing requirements developed in Phase I and update requirements based on new information Develop specifications for an airframe demonstrator model Develop specifications for an aeroacoustic phased array to be used during the demonstrator test Update sensor designs and sensor packaging designs per requirements update, airframe array demonstrator model specification, and aeroacoustic phased arrays specification Update array processing algorithm proposals per requirements update Design modified components/parts needed to install in-model sensors in an existing airframe demonstrator model Fabricate and package dynamic pressure sensors ready for installation in the demonstrator model Fabricate and package array microphones ready for installation in the aeroacoustic array Calibrate dynamic pressure sensors and instrument the demonstrator model Calibrate array microphones and instrument the aeroacoustic array Implement the proposed array processing algorithms and software modifications to improve data visualization and analysis processes Conduct a demonstrator test Process demonstrator test data using newly developed array processing algorithms Determine advantages and limitations of the new algorithms Deliverables: Final New Technology Summary Report (NTSR), Technical Report, Summary Chart, TABA Report

The proposed instrumentation technology has the potential to be usable in multiple NASA facilities as well as implemented across government-owned, industry and academic institution test facilities. Potential NASA applications include use in the 14x22-Foot Subsonic Tunnel, National Transonic Facility, and Basic Aerodynamic Research Tunnel at Langley, the 7x10 and 40x80-Foot tunnels at Ames, and the 9x15 tunnel and Aeroacoustc Propulsion Facility at Glenn. Other government agencies (e.g., DOD, DARPA) and industry manufacturers (e.g., Boeing, Lockheed, GE) have similar needs to NASA. Specifically, researchers and test engineers are limited in their ability to collect high-fidelity aeroacoustic measurements in wind tunnel testing due to sensor packaging limitations and cost.

This is a mature technology (TRL 7+) — the realistic path in is usually NASA's Technology Transfer Program: licensing an existing NASA patent, or a Space Act Agreement to use NASA facilities/expertise directly. NASA also runs a startup licensing program with no upfront fee for companies formed to commercialize a specific NASA technology.

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