Abstract: A loading pad to be attached to a specimen to apply a load to the specimen includes: a back skin on which the load is applied; an elastic body that is provided between the back skin and the specimen; and an inserted member that is provided between the elastic body and the specimen. The back skin, the elastic body, and the inserted member are bonded as one unit. The inserted member is less rigid than the specimen, and is more rigid than the elastic body.

Abstract: The present invention comprises: a fatigue estimation unit that estimates the fatigue life of a prescribed area of a fuselage, on the basis of the level of damage in the prescribed area during operation; a determination unit that determines whether the estimated fatigue life will be reached after a prescribed period of time has elapsed; a repair determination unit that determines that repair of the fuselage is unnecessary if a determination is made that the estimated fatigue life will be reached after the prescribed period of time has elapsed, and that determines that the fuselage is to be repaired if a determination is made that the estimated fatigue life will be reached within the prescribed period of time; and a selection unit that, if a determination is made that the fuselage is to be repaired, selects a repair method corresponding to the detected degree of damage in the prescribed area.

Abstract: To provide a repairing member, a repair structure, and a damage detection method that enable accurate detection of damage that occurs in a repairing member and a repairing target member. The repair structure includes a skin in which an opening is formed, and a plate-like repairing member fixed to the skin to cover the opening. The repairing member has a recess formed on a contact face side in contact with the skin, and an ultrasonic search unit is placed inside the recess. The ultrasonic search unit is placed so as to be in contact with both the repairing member and the skin.

Abstract: To detect damages of aircrafts using a small number of sensors. Provided with a category generation unit that categories usage environment information set that is determined based on aircraft types associated with the aircrafts and flight conditions associated with the aircrafts and that indicates usage environments of the airframes of the aircrafts into a plurality of categories in such a way that similar usage environment information set is categorized into the same category; an extraction unit that extracts a category in which an aircraft to be diagnosed is categorized; and a determination unit that determines the arrangement positions of measurement devices relative to the aircraft to be diagnosed, based on previous data that changes for each of the usage environments and that has been obtained when one of the aircrafts has been operated under a usage environment corresponding to the categorized category.

Abstract: The present invention comprises: a fatigue estimation unit that estimates the fatigue life of a prescribed area of a fuselage, on the basis of the level of damage in the prescribed area during operation; a determination unit that determines whether the estimated fatigue life will be reached after a prescribed period of time has elapsed; a repair determination unit that determines that repair of the fuselage is unnecessary if a determination is made that the estimated fatigue life will be reached after the prescribed period of time has elapsed, and that determines that the fuselage is to be repaired if a determination is made that the estimated fatigue life will be reached within the prescribed period of time; and a selection unit that, if a determination is made that the fuselage is to be repaired, selects a repair method corresponding to the detected degree of damage in the prescribed area.

Abstract: A damaged portion determination device includes: a damage identification unit that identifies a damaged portion of an airframe of an aircraft; a position identification unit that identifies a reference position inside the airframe of the aircraft; and a damaged portion presentation unit that superimposes and presents an imaging result resulting from imaging of a state inside the airframe of the aircraft at the reference position by an imaging device, internal structural data representing an internal structure of the aircraft, and position information about the damaged portion relative to the reference position.

Abstract: To provide a repairing member, a repair structure, and a damage detection method that enable accurate detection of damage that occurs in a repairing member and a repairing target member. The repair structure includes a skin in which an opening is formed, and a plate-like repairing member fixed to the skin to cover the opening. The repairing member has a recess formed on a contact face side in contact with the skin, and an ultrasonic search unit is placed inside the recess. The ultrasonic search unit is placed so as to be in contact with both the repairing member and the skin.

Abstract: Provided is an optical fiber characteristics measurement device that is provided with: a light source for emitting laser light modulated by a specified modulation frequency; an incident means for receiving the laser light from the light source as continuous light and pulse light from one end and the other end of an optical fiber, respectively; and a light detector for detecting light emitted from the optical fiber, the optical fiber characteristics measurement device measuring the characteristics of the optical fiber using the detection results of the light detector, wherein the optical fiber characteristics measurement device is characterized in being provided with a synchronous detector that extracts, from among the detection signals output from the light detector, detection signals obtained by detecting the light in the vicinity of a measurement point set in the optical fiber, and synchronously detects the extracted detection signals using a synchronization signal having a specified period.

Abstract: A bonding method and a bonding tool that enable quick and reliable bonding of an optical fiber to a structural body by a simple process, and a method for producing a structural body are provided. In an optical fiber (1), a strand is coated with a coating portion of a thermoplastic resin. At least one portion of the coating portion is heated and melted by a heater (14). The portion where the thermoplastic resin is melted of the optical fiber (1) and a surface of a structural body (17) are brought into contact with each other in a state in which the thermoplastic resin is melted. A molding roller (15) pressure-bonds the optical fiber (1) to the surface of the structural body (17) . The thermoplastic, resin is then cooled and cured, so that the optical fiber (1) is bonded to the structural body (17).

Abstract: An optical fiber characteristic measuring device of the present invention includes: a light source which emits laser light modulated at a predetermined modulation frequency; an incident section which causes the laser light from the light source as continuous light and pulsed light to be incident from one end and other end of an optical fiber respectively; a timing adjuster which causes light emitted from the optical fiber to pass therethrough at a predetermined timing; and a light detector which detects the light which passes through the timing adjuster, and measures a characteristic of the optical fiber by using a detection result of the light detector, and the device includes: a synchronous detector which synchronously detects the detection result of the light detector by using a synchronization signal having a predetermined frequency; and a frequency setter which changes the frequency of the synchronization signal in a case where the modulation frequency at the light source is an integer multiple of the fr

Abstract: Provided is an optical fiber characteristics measurement device that is provided with: a light source for emitting laser light modulated by a specified modulation frequency; an incident means for receiving the laser light from the light source as continuous light and pulse light from one end and the other end of an optical fiber, respectively; and a light detector for detecting light emitted from the optical fiber, the optical fiber characteristics measurement device measuring the characteristics of the optical fiber using the detection results of the light detector, wherein the optical fiber characteristics measurement device is characterized in being provided with a synchronous detector that extracts, from among the detection signals output from the light detector, detection signals obtained by detecting the light in the vicinity of a measurement point set in the optical fiber, and synchronously detects the extracted detection signals using a synchronization signal having a specified period.

Abstract: An optical fiber characteristic measuring device of the present invention includes: a light source which emits laser light modulated at a predetermined modulation frequency; an incident section which causes the laser light from the light source as continuous light and pulsed light to be incident from one end and other end of an optical fiber respectively; a timing adjuster which causes light emitted from the optical fiber to pass therethrough at a predetermined timing; and a light detector which detects the light which passes through the timing adjuster, and measures a characteristic of the optical fiber by using a detection result of the light detector, and the device includes: a synchronous detector which synchronously detects the detection result of the light detector by using a synchronization signal having a predetermined frequency; and a frequency setter which changes the frequency of the synchronization signal in a case where the modulation frequency at the light source is an integer multiple of the fr