Measuring and testing – Specimen stress or strain – or testing by stress or strain... – By loading of specimen
Patent
1991-07-31
1993-02-09
Myracle, Jerry W.
Measuring and testing
Specimen stress or strain, or testing by stress or strain...
By loading of specimen
73767, 324718, G01N 1908
Patent
active
051845164
ABSTRACT:
A strain, crack and acoustic emission conformal structural health monitoring circuit with integral preprocessor and provisions for connectorization to a central processing system includes a strain gauge (11) having crack sensing traces (21), (23), and (25) sandwiched between a bottom layer (13) and a top layer (39). Strain gauge (11) is attached to an aircraft structural surface (51) to be monitored. Successive alternating layers of interconnecting sheet layers (61) and dielectric layers (63) joined by successive layers of non-structural adhesive (65) are added sufficient to effectively attenuate any stress forces, and forces directly from the strain and cracks, from traveling upward from the aircraft structural surface (51). A metalization layer (47) tops the successive layers and supports an integrated circuit (43) which may be multi-chip hybrid package, discretely packaged components or conformally coated chip/circuit assemblies, and provides a means of interconnect to and protection from the ambient environment.
REFERENCES:
patent: 4546652 (1985-10-01), Virkar et al.
patent: 4835466 (1989-05-01), Maly et al.
patent: 5086652 (1992-02-01), Kropp
Blazic Ernest S.
Bueker Robert A.
Farwell William D.
Smalanskas Joseph P.
Waters Lynn O.
Alkov L. A.
Denson-Low W. K.
Hughes Aircraft Company
Myracle Jerry W.
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