PURPOSE: To obtain a structure monitor system for detecting distortions and cracks of a surface of a structure.
CONSTITUTION: A structure soundness monitoring circuit to which distortions, cracks and acoustic emissions are applied contains a distortion gauge 11 having crack detection traces 21, 23, 25 interposed between a lowermost layer 13 and an uppermost layer 39. The distortion gauge 11 is fitted on a surface of an airplane to be monitored. A coupling layer 61 and an insulation layer 63 laminated alternately and coupled with adhesives 65 are used so that any stress or even a force received directly from distortions and cracks is not transmitted upwardly from a surface 51 of an airplane. A metalized layer 47 is located at an uppermost part of continuous layers, supports an IC 43, and provides coupling means to the outside and protection means from the outside.
ROBAATO EE BIYUUKAA
RIN OO UOOTAASU
UIRIAMU DEII FUAAUERU
JIYOSEFU SUMARANSUKASU
| JPS59131554A | 1984-07-28 |