Small Business Innovation Research/Small Business Tech Transfer
Fiber Optic Pressure Sensor Array
Project Description
VIP Sensors proposes to develop a Fiber Optic Pressure Sensor Array System for measuring air flow pressure at multiple points on the skin of aircrafts for Flight Load Test applications. The array consists of multiple micro-miniature optical MEMS pressure sensors interconnected by a common optic fiber to an Interrogation Module located inside the airplane. The proposed optical pressure sensors are practically flat, light weight, fully passive (no electrical power), and EMI/RFI immune, they exhibit superior performance regarding accuracy, dynamic range and noise. They are inherently self identifiable; the interrogation system knows what data belongs to what sensor. The proposed sensor array technology is applicable to different types of optical sensors (accelerometers, strain, temperature, etc). Each sensor in the array is designed to work at preset optical wavelengths; they are read by the Interrogation Module using Wave Division and Time Division Multiplexing. Testing of aircrafts requires a large numbers of sensors. Each sensor needs four to six wires to interconnect to signal conditioners. For large measuring systems, this means very large numbers of wires that add weight and occupy space. The proposed FO sensor array system not only has the potential to significantly improve pressure measurements for Flight Load Testing, but its novel technology of micro-miniature networking sensors will benefit many other aircraft ground and flight testing applications.
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Anticipated Benefits
The Fiber Optic Pressure Sensor Array System is applicable to many other fields where passive sensors of small size, high accuracy, and networking features are important. F/O Sensor Array technology developed in this program is directly applicable to other types of inertial sensors such as optical accelerometers, microphones, etc. Flight Testing Thousands of sensors to test and qualify aircraft; the networking feature drastically reduces cabling and testing costs. Wind Tunnel Testing Hundred of pressure and vibration measurement channels are used world wide Airplane and Satellite Monitoring Large number of sensors of different types are used for on-board monitoring. Naval Ship Monitoring Thousands of sensors are used on board military and commercial ships. Helicopter Condition Based Monitoring - Hundreds of sensors are used in Health Usage Monitoring Systems on board helicopters. Structural Testing Hundreds of sensors are used to test the modal behavior of airplanes, satellites, missiles and other structures.
Applications are in flight and ground/wind tunnel testing of aircrafts where surface pressure measurements are needed. The proposed system, for many applications, is a better alternative to the Electronic Scanner Pressure system, which are used across NASA wind tunnel facilities and flight test programs: 1. Subsonic Facilities: Low Speed Wind Tunnel at GRC, Subsonic Tunnel and Vertical Spin Tunnel at LaRC 2. Transonic Facilities: National Transonic Facility and Transonic Dynamics Tunnel at LaRC, Unitary Plan Facility at ARC 3. Supersonic Facilities: Supersonic Wind Tunnels at GRC and ARC, Unitary Plan Wind Tunnel (UPWT) at LaRC's 4. Flight Loads Laboratory (FLL) at Dryden Flight Research Center (DFRC). NASA fight & wind tunnel test scientists have shown a high degree of interest on the system as demonstrated by the participation of three Technology Infusion Application Advisers listed below: Organization Transition Program Mission Directive James Bell NASA/ARC Moffett Fundamental Aeronautics Aeronautics Research David Star Facility Manag. Planning Office Wind Tunnel Testing Aeronautics Research Allen R. Parker NASA Dryden SOFIA, Ikhana, 853 (one of Dryden's F-18), Global Hawk Aeronautics Research More »
Applications are in flight and ground/wind tunnel testing of aircrafts where surface pressure measurements are needed. The proposed system, for many applications, is a better alternative to the Electronic Scanner Pressure system, which are used across NASA wind tunnel facilities and flight test programs: 1. Subsonic Facilities: Low Speed Wind Tunnel at GRC, Subsonic Tunnel and Vertical Spin Tunnel at LaRC 2. Transonic Facilities: National Transonic Facility and Transonic Dynamics Tunnel at LaRC, Unitary Plan Facility at ARC 3. Supersonic Facilities: Supersonic Wind Tunnels at GRC and ARC, Unitary Plan Wind Tunnel (UPWT) at LaRC's 4. Flight Loads Laboratory (FLL) at Dryden Flight Research Center (DFRC). NASA fight & wind tunnel test scientists have shown a high degree of interest on the system as demonstrated by the participation of three Technology Infusion Application Advisers listed below: Organization Transition Program Mission Directive James Bell NASA/ARC Moffett Fundamental Aeronautics Aeronautics Research David Star Facility Manag. Planning Office Wind Tunnel Testing Aeronautics Research Allen R. Parker NASA Dryden SOFIA, Ikhana, 853 (one of Dryden's F-18), Global Hawk Aeronautics Research More »
Primary U.S. Work Locations and Key Partners
| Organizations Performing Work | Role | Type | Location |
|---|---|---|---|
| VIP Sensors | Lead Organization |
Industry
Minority-Owned Business
|
San Juan Capistrano, California |
Armstrong Flight Research Center
(AFRC)
|
Supporting Organization | NASA Center | Edwards, California |
Primary U.S. Work Locations
-
California
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