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Digital angular position sensor using wavelength division multiplexingFuture aircraft will use fly-by-light control systems with fiber-linked optical sensors for such measurands as temperature, pressure, and linear and angular position. A digital optical sensor is described which was developed to transmit the angular position of such slowly rotating parts as a throttle of fuel flow control valve on an aircraft. The sensor employs a reflective code plate with ten channels providing a resolution of 0.35 degrees. Two light-emitting diodes with overlapping spectra are used as light sources. A single microoptic multiplexer-demultiplexer composed of a GRIN rod lens and a miniature grating is used to disperse the spectrum and recombine the spectral components from each channel after reflection by the code plate. The results of preliminary environmental tests of this unit are discussed. The sensor has been operated for brief periods of time between -60 C and +125 without adverse effects. Preliminary vibration tests indicate that the unit will work properly at the maximum vibration levels expected in a jet-engine environment.
Document ID
19910034957
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Fritsch, Klaus
(John Carroll University Cleveland, OH, United States)
Beheim, Glenn
(John Carroll Univ. Cleveland, OH, United States)
Sotomayor, Jorge
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1990
Subject Category
Aircraft Instrumentation
Accession Number
91A19580
Funding Number(s)
CONTRACT_GRANT: NAG3-571
Distribution Limits
Public
Copyright
Other

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