Rapid technology assessment via unified deployment of global optical and virtual diagnostics

This paper discusses recent developments in rapid technology assessment resulting from an active collaboration between researchers at the Air Force Research Laboratory (AFRL) at Wright Patterson Air Force Base (WPAFB) and the NASA Langley Research Center (LaRC). This program targets the unified development and deployment of global measurement technologies coupled with a virtual diagnostic interface to enable the comparative evaluation of experimental and computational results. Continuing efforts focus on the development of seamless data translation methods to enable integration of data sets of disparate file format in a common platform. Results from a successful low-speed wind tunnel test at WPAFB in which global surface pressure distributions were acquired simultaneously with model deformation and geometry measurements are discussed and comparatively evaluated with numerical simulations. Intensity- and lifetime-based pressure-sensitive paint (PSP) and projection moire interferometry (PMI) results are presented within the context of rapid technology assessment to enable simulation-based R&D.

[1]  Gary A. Fleming,et al.  Measurement of rotorcraft blade deformation using projection moire interferometry , 1998, Other Conferences.

[2]  J. W. Holmes,et al.  Analysis of radiometric, lifetime and fluorescent lifetime imaging for pressure sensitive paint , 1998, The Aeronautical Journal (1968).

[3]  Christopher A. Martin,et al.  Contributions of the NASA Langley Research Center to the DARPA/AFRL/NASA/ Northrop Grumman Smart Wing Program , 2003 .

[4]  A Fleming Gary,et al.  Projection Moire Interferometry Measurements of Micro Air Vehicle Wings , 2001 .

[5]  Kazunori Mitsuo,et al.  Development of Lifetime Imaging System for Pressure-Sensitive Paint , 2002 .

[6]  R. H. Engler,et al.  DLR PSP system intensity and lifetime measurements , 1997, ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities.

[7]  Luther N. Jenkins,et al.  Projection moire interferometry measurements of micro air vehicle wings , 2001, SPIE Optics + Photonics.

[8]  R Waszak Martin,et al.  Stability and Control Properties of an Aeroelastic Fixed Wing Micro Aerial Vehicle , 2001 .

[9]  Gary A. Fleming,et al.  Projection Moire Interferometry for Rotorcraft Applications: Deformation Measurements of Active Twist Rotor Blades , 2002 .

[10]  Alpheus W. Burner,et al.  Deformation measurements of smart aerodynamic surfaces , 1999, Optics & Photonics.

[11]  J. H. Bell,et al.  Image registration for pressure-sensitive paint applications , 1996 .

[12]  Gary A. Fleming,et al.  Unified Instrumentation: Examining the Simultaneous Application of Advanced Measurement Techniques for Increased Wind Tunnel Testing Capability , 2002 .

[13]  Gregory J. Fiechtner,et al.  Evaluation of new camera architectures for pressure sensitive paint measurements , 2000 .

[14]  J. Callis,et al.  Surface pressure field mapping using luminescent coatings , 1993 .

[15]  Krzysztof Patorski,et al.  Handbook of the moiré fringe technique , 1993 .

[16]  J. Roy,et al.  Understanding Web services , 2001 .

[17]  J. Callis,et al.  Luminescent barometry in wind tunnels , 1990 .

[18]  M. Carbonaro,et al.  von Karman Institute for Fluid Dynamics , 2004 .

[19]  J. Bell,et al.  Pressure-sensitive paint in aerodynamic testing , 1993 .