HONEYCOMB SANDWICH STRUCTURE INCLUDING OPTICAL FIBER SENSOR, AND METHOD OF MANUFACTURING THE SAME

PROBLEM TO BE SOLVED: To provide a honeycomb sandwich structure including an optical fiber sensor, in which an adherend is bonded to a surface with high flatness and the soundness of the adherend and adhesion layer is evaluated with high accuracy.SOLUTION: In a honeycomb sandwich structure where a f...

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Hauptverfasser:	SEKINE KAZUFUMI, SEKO HIROMI, TAKEYA HAJIME
Format:	Patent
Sprache:	eng
Schlagworte:	AIRCRAFT ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVEREDIN A SINGLE OTHER SUBCLASS AVIATION COSMONAUTICS DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING ORREPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLYADAPTED FOR USE IN CONNECTION WITH AIRCRAFT HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFTCOMPONENTS, NOT OTHERWISE PROVIDED FOR MEASURING MEASURING ANGLES MEASURING AREAS MEASURING IRREGULARITIES OF SURFACES OR CONTOURS MEASURING LENGTH, THICKNESS OR SIMILAR LINEARDIMENSIONS MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR PERFORMING OPERATIONS PHYSICS TARIFF METERING APPARATUS TESTING TRANSPORTING
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Beschreibung
Zusammenfassung:	PROBLEM TO BE SOLVED: To provide a honeycomb sandwich structure including an optical fiber sensor, in which an adherend is bonded to a surface with high flatness and the soundness of the adherend and adhesion layer is evaluated with high accuracy.SOLUTION: In a honeycomb sandwich structure where a fiber-reinforced plastic skin material (10) and a honeycomb core (30) are bonded together with an adhesion layer (21), an optical fiber sensor (40) formed with a fiber Bragg grating part (42) whose Bragg wavelength of reflection spectrum changes according to distortion is embedded in the adhesion layer (21) bonding the skin material (10) and honeycomb core (30) together without the occurrence of holes.