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: This evaluating method is an evaluating method for evaluating an assembly (50) provided with a reinforced member (60) and a reinforcing member (70), and includes: a step of introducing incident light into a first optical fiber (20) extending between a first composite layer and a second composite layer and detecting outgoing light therefrom to measure a first strain distribution, and introducing incident light into a second optical fiber (30) extending between the second composite layer and a third composite layer and detecting outgoing light therefore to measure a second strain distribution; and a step of acquiring the shape of wrinkles at the surface (60s) of the reinforced member (60) from the first strain distribution and the second strain distribution.

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 debonding detecting method detects debonding of an adhering portion at which an adhering object adheres to an adherend. An optical fiber sensor is provided on the adherend adjacent to the adhering object. A longitudinal direction of the optical fiber sensor is along a direction in which the adhering object extends. Reference strain data of a strain measured by the optical fiber sensor is prepared in advance when a load is applied to the adherend in a reference state in which debonding of the adhering portion does not occur. The debonding detecting method includes: applying a load to the adherend; measuring a strain of the adherend by the optical fiber sensor; and the determining presence or absence of debonding based on comparison result obtained by comparing measured strain data measured in the measuring and the reference strain data.

Abstract: This evaluating method is an evaluating method for evaluating an assembly (50) provided with a reinforced member (60) and a reinforcing member (70), and includes: a step of introducing incident light into a first optical fiber (20) extending between a first composite layer and a second composite layer and detecting outgoing light therefrom to measure a first strain distribution, and introducing incident light into a second optical fiber (30) extending between the second composite layer and a third composite layer and detecting outgoing light therefore to measure a second strain distribution; and a step of acquiring the shape of wrinkles at the surface (60s) of the reinforced member (60) from the first strain distribution and the second strain distribution.

Abstract: An aircraft health diagnostic device is provided with a control unit that carries out structural health monitoring of a structure of an aircraft. The control unit has a first risk assessment unit that assesses the risk of damage occurring in the structure on the basis of a correlation between reference data stored in a storage unit and a signal data set based on measurement data obtained through measurement carried out by a measuring instrument, a second risk assessment unit that assesses the risk of damage occurring in the structure on the basis of the time-sequence change in the behavior of the signal data set, and a maintenance assessment unit that assesses the life, repair timing, and a maintenance plan of the structure on the basis of the time-sequence change in the behavior of the signal data set.

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: A vehicle rear structure includes a bottom cover disposed rearward of a rear wheel well in a vehicle front-rear direction. The bottom cover includes an air inlet into which air that has flowed from a front side toward a rear side in the vehicle front-rear direction is taken such that the air flows outward in a vehicle-width direction. The bottom cover further includes an air outlet provided at a position outward of the air inlet in the vehicle-width direction. The air outlet is an air outlet from which the air flows from the air inlet outward in the vehicle-width direction is discharged outward in the vehicle-width direction and downward in a vehicle-height direction.

Abstract: The purpose of the present invention is to provide a bonded structure, a method for manufacturing the same, and a bonding state detection method which are capable of determining whether or not members are bonded together appropriately. A bonded structure 10 includes a laminated sheet 12A, a laminated sheet 12B, an adhesive 14 that bonds the laminated sheet 12A and the laminated sheet 12B together, and a distributed optical fiber 16 sandwiched between the laminated sheet 12A and the laminated sheet 12B. The cross-sectional shape of the distributed optical fiber 16 is deformed in accordance with the bonding state.

Abstract: In a debonding detecting method, debonding of an adhering portion at which a stringer adheres to a skin is detected. An optical fiber sensor is provided on the skin so as to be adjacent to the stringer. The optical fiber sensor is provided so that a longitudinal direction of the optical fiber sensor is along a longitudinal direction of the stringer. Reference strain data of a strain in a reference state in which debonding of the adhering portion does not occur is prepared in advance. The debonding detecting method includes a load applying step in which a load is applied to the skin, a strain measuring step in which the optical fiber sensor measures a strain of the skin, and a debonding determining step in which presence or absence of debonding is determined based on a comparison result obtained by comparing measured strain data measured in the strain measuring step and the reference strain data.

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: A bonded structure includes a first member, a second member, an adhesive that bonds the first member and the second member together, and an optical fiber sandwiched between the first member and the second member. When pressure is applied to the optical fiber only from a predetermined direction, the sectional shape of the optical fiber changes to an elliptical shape, so that birefringence occurs, whereby the shape of the light spectrum changes so as to have multiple peaks. The optical fiber is used as a sensor for detecting the bonding condition between the first member and the second member based on the birefringence.

Abstract: A vehicle rear structure includes a bottom cover disposed rearward of a rear wheel well in a vehicle front-rear direction. The bottom cover includes an air inlet into which air that has flowed from a front side toward a rear side in the vehicle front-rear direction is taken such that the air flows outward in a vehicle-width direction. The bottom cover further includes an air outlet provided at a position outward of the air inlet in the vehicle-width direction. The air outlet is an air outlet from which the air flows from the air inlet outward in the vehicle-width direction is discharged outward in the vehicle-width direction and downward in a vehicle-height direction.

Abstract: The purpose of the present invention is to provide a bonded structure, a method for manufacturing the same, and a bonding state detection method which are capable of determining whether or not members are bonded together appropriately. A bonded structure 10 includes a laminated sheet 12A, a laminated sheet 12B, an adhesive 14 that bonds the laminated sheet 12A and the laminated sheet 12B together, and a distributed optical fiber 16 sandwiched between the laminated sheet 12A and the laminated sheet 12B. The cross-sectional shape of the distributed optical fiber 16 is deformed in accordance with the bonding state.

Abstract: A bonded structure (10) includes a laminate (12A), a laminate (12B), an adhesive (14) that bonds together the laminate (12A) and the laminate (12B), and an optical fiber (16) sandwiched between the laminate (12A) and the laminate (12B). When a pressure is applied to the optical fiber (16) only from a predetermined direction, the sectional shape of the optical fiber (16) changes to an elliptical shape, so that birefringence occurs, whereby the shape of the light spectrum changes so as to have multiple (e.g., two) peaks. The optical fiber (16) is used as a sensor for detecting the bonding condition between the laminate (12A) and the laminate (12B) based on this birefringence. Thus, with the bonded structure 10, it is possible to determine whether members are bonded together appropriately.

Abstract: A compound represented by the following Formula (1) that is effective for the treatment of Paget's disease of bone or hypercalcemia or a medically acceptable solvate thereof; [wherein R1 refers to hydrogen atom, C1-C6 alkyl group optionally substituted with hydrogen group or C1-C6 alkoxy group optionally substituted with hydroxyl group, R2a and R2b refer to hydrogen atom, C1-C10 alkyl group optionally substituted with hydroxyl group, C6-C10 aryl group optionally substituted with hydroxyl group or C7-C12 aralkyl group optionally substituted with a hydroxyl group, or are combined to represent ethylene group. However, a compound in which R1 is a hydrogen atom or a methyl group and R2a and R2b are hydrogen atoms is excluded].

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: A twin-shaft gas turbine, which has a gas generator including a compressor, a combustor, and a high-pressure turbine, is configured to make a first control mode and a second control mode selectively useable for control of the gas generator. In addition, in the first control mode, an IGV angle in the compressor is controlled in accordance with a corrected shaft rotation speed of the gas generator, and in the second control mode, the IGV angle is controlled to maintain a constant gas generator shaft rotation speed. Furthermore, the first control mode is used to start, to stop, and to operate the turbine under fixed or lower load conditions, and that the second control mode is used under operational states other than those to which the first control mode is applied.