Abstract: According to one implementation, a composite material structure includes a corrugated stringer and a panel. The corrugated stringer has a corrugated structure including portions each having hat-shaped cross section. The corrugated stringer is made of a composite material. The panel is integrated with the corrugated stringer. The panel is made of a composite material. Further, according to one implementation, a manufacturing method of a composite material structure includes: setting a textile on a laminated body of prepregs; and producing the composite material structure by covering the laminated body with a bagging film, forming a vacuum state in a space covered with the bagging film, impregnating the textile with the resin, and thermal curing of the laminated body of the prepregs. The laminated body is a panel before curing. The textile has a structure corresponding to a corrugated stringer.

Abstract: According to one implementation, a method of producing an ultrasonic inspection system includes creating design information on the ultrasonic inspection system and assembling the ultrasonic inspection system based on the design information. The design information includes numbers, positions and directions of at least one ultrasonic sensor and at least one ultrasonic transducer. The design information is created by an optimization calculation of which at least one parameter includes at least one of the numbers, positions and directions of the at least one ultrasonic sensor and the at least one ultrasonic transducer. The optimization calculation includes a simulation of an ultrasonic inspection for detecting a defect by the ultrasonic inspection system having the at least one ultrasonic sensor and the at least one ultrasonic transducer. The simulation is performed using a model simulating an object of the ultrasonic inspection.

Abstract: Aspects of the subject technology relate to a landing gear of a rotorcraft including two skid tubes and a cross tube. The cross tube couples the skid tubes to each other and attaches the skid tubes to a fuselage of the rotorcraft. At least a part of the cross tube is made of a composite material to achieve sufficient absorption of energy while preventing the fuselage from coming into contact with a ground surface, at the time of landing the rotorcraft, under a more satisfactory condition. The rotorcraft includes the landing gear to achieve sufficient absorption of energy while preventing the fuselage from coming into contact with the ground surface, at the time of landing the rotorcraft, under a more satisfactory condition.

Abstract: According to one implementation, a composite material structure includes a corrugated stringer and a panel. The corrugated stringer has a corrugated structure including portions each having hat-shaped cross section. The corrugated stringer is made of a composite material. The panel is integrated with the corrugated stringer. The panel is made of a composite material. Further, according to one implementation, a manufacturing method of a composite material structure includes: setting a textile on a laminated body of prepregs; and producing the composite material structure by covering the laminated body with a bagging film, forming a vacuum state in a space covered with the bagging film, impregnating the textile with the resin, and thermal curing of the laminated body of the prepregs. The laminated body is a panel before curing. The textile has a structure corresponding to a corrugated stringer.

Abstract: According to one implementation, a method of producing an ultrasonic inspection system includes creating design information on the ultrasonic inspection system and assembling the ultrasonic inspection system based on the design information. The design information includes numbers, positions and directions of at least one ultrasonic sensor and at least one ultrasonic transducer. The design information is created by an optimization calculation of which at least one parameter includes at least one of the numbers, positions and directions of the at least one ultrasonic sensor and the at least one ultrasonic transducer. The optimization calculation includes a simulation of an ultrasonic inspection for detecting a defect by the ultrasonic inspection system having the at least one ultrasonic sensor and the at least one ultrasonic transducer. The simulation is performed using a model simulating an object of the ultrasonic inspection.

Abstract: According to one implementation, a landing gear of a rotorcraft includes two skid tubes and a cross tube. The cross tube couples the skid tubes to each other and attaches the skid tubes to a fuselage of the rotorcraft. At least a part of the cross tube is made of a composite material so that it becomes possible to achieve both sufficient absorption of energy and preventing the fuselage from coming into contact with a ground surface, at the time of landing the rotorcraft, under a more satisfactory condition. Further, according to one implementation, a rotorcraft includes the above-mentioned landing gear so that it becomes possible to achieve both sufficient absorption of energy and preventing a fuselage from coming into contact with a ground surface, at the time of landing the rotorcraft, under a more satisfactory condition.

Abstract: An aircraft wing load alleviation device is to be provided to an aircraft having a body, a main wing, and an elongated supporting member with an end fixed to the body and another end fixed to the main wing to support the main wing. The aircraft wing load alleviation device alleviates a load acting on the main wing, and includes a load detector, an actuator, and a controller. The load detector detects the load acting on the main wing. The actuator is provided to the supporting member and applies a load in a longitudinal direction of the supporting member. The controller controls, when the load acting on the main wing is detected, operation of the actuator to make the actuator apply the load to the supporting member in a direction opposite to a direction of a load applied on the supporting member as a result of the detected load.

Abstract: According to one implementation, a composite material structure includes a corrugated stringer and a panel. The corrugated stringer has a corrugated structure including portions each having hat-shaped cross section. The corrugated stringer is made of a composite material. The panel is integrated with the corrugated stringer. The is made of a composite material. Further, according to one implementation, a manufacturing method of a composite material structure includes: setting a textile on a laminated body of prepregs; and producing the composite material structure by covering the laminated body with a bagging film, forming a vacuum state in a space covered with the bagging film, impregnating the textile with the resin, and thermal curing of the laminated body of the prepregs. The laminated body is a panel before curing. The textile has a structure corresponding to a corrugated stringer.

Abstract: An aircraft wing load alleviation device is to be provided to an aircraft having a body, a main wing, and an elongated supporting member with an end fixed to the body and another end fixed to the main wing to support the main wing. The aircraft wing load alleviation device alleviates a load acting on the main wing, and includes a load detector, an actuator, and a controller. The load detector detects the load acting on the main wing. The actuator is provided to the supporting member and applies a load in a longitudinal direction of the supporting member. The controller controls, when the load acting on the main wing is detected, operation of the actuator to make the actuator apply the load to the supporting member in a direction opposite to a direction of a load applied on the supporting member as a result of the detected load.

Abstract: According to one implementation, a structure for an aircraft includes a first structural member, a second structural member coupled to the first structural member, a fastener and a conductive object. The fastener couples the first structural member to the second structural member. The fastener is inserted into an insertion hole formed in a portion where the first structural member is overlapped with the second structural member. The fastener is in electrically non-contact with the first and second structural members in the insertion hole. The conductive object is embedded inside at least either one of the first and second structural members. The conductive object prevents a spark between the fastener and each of the first and second structural members by forming a current pathway that leads current, flowing inside the at least either one of the first and second structural members, to the other structural member.

Abstract: According to one implementation, a method of making design information of an aircraft structural object, executed by a computer, includes: setting at least one parameter as a variable for an optimization calculation which minimizes a weight of the structural object composing an aircraft; setting at least one allowable range for at least a strength of the structural object corresponding to the at least one parameter; and calculating an optimal value of the weight of the structural object and a value of the at least one parameter by the optimization calculation. The at least one parameter expresses the design information of the structural object. The at least one allowable range is set as at least one constraint condition of the optimization calculation. The value of the at least one parameter corresponds to the optimal value and meets the at least one allowable range.

Abstract: A joint analyzing method includes: performing a data measurement; performing a detailed analysis; performing a simplified analysis; performing a first repetition analysis in which the detailed analysis is repeated while modifying a first analysis model in which geometry of a joint surrounding region is modeled and an analysis technique in the detailed analysis, until a data measurement result and a detailed analysis result are brought into agreement; and performing a second repetition analysis in which the simplified analysis that takes into consideration an initial internal load of at least one junction in a load non-applied state obtained in the first repetition analysis is repeated while modifying a second analysis model rougher in element division of the geometry than the first analysis model and an analysis technique in the simplified analysis, until the data measurement result and a simplified analysis result are brought into agreement.

Abstract: According to one implementation, a method of making design information of an aircraft structural object, executed by a computer, includes: setting at least one parameter as a variable for an optimization calculation which minimizes a weight of the structural object composing an aircraft; setting at least one allowable range for at least a strength of the structural object corresponding to the at least one parameter; and calculating an optimal value of the weight of the structural object and a value of the at least one parameter by the optimization calculation. The at least one parameter expresses the design information of the structural object. The at least one allowable range is set as at least one constraint condition of the optimization calculation. The value of the at least one parameter corresponds to the optimal value and meets the at least one allowable range.

Abstract: According to one implementation, a structure for an aircraft includes a first structural member, a second structural member coupled to the first structural member, a fastener and a conductive object. The fastener couples the first structural member to the second structural member. The fastener is inserted into an insertion hole formed in a portion where the first structural member is overlapped with the second structural member. The fastener is in electrically non-contact with the first and second structural members in the insertion hole. The conductive object is embedded inside at least either one of the first and second structural members. The conductive object prevents a spark between the fastener and each of the first and second structural members by forming a current pathway that leads current, flowing inside the at least either one of the first and second structural members, to the other structural member.

Abstract: A joint analyzing method includes: performing a data measurement; performing a detailed analysis; performing a simplified analysis; performing a first repetition analysis in which the detailed analysis is repeated while modifying a first analysis model in which geometry of a joint surrounding region is modeled and an analysis technique in the detailed analysis, until a data measurement result and a detailed analysis result are brought into agreement; and performing a second repetition analysis in which the simplified analysis that takes into consideration an initial internal load of at least one junction in a load non-applied state obtained in the first repetition analysis is repeated while modifying a second analysis model rougher in element division of the geometry than the first analysis model and an analysis technique in the simplified analysis, until the data measurement result and a simplified analysis result are brought into agreement.