Abstract: A load calculator includes a coefficient storage, a replacement deriver, and an internal-load deriver. The storage stores a first coefficient, an internal load acting on a target point in a target member when a unit load acts on a concentrated load point in the target member along one of three orthogonal axes, and as a second coefficient, an internal load acting on the target point when a unit moment acts on the concentrated load point around one of the axes. The replacement deriver derives a replacement load and moment by replacing an external load acting on the target member with six force components acting on the concentrated load point. The internal load deriver derives an internal load acting on any target point with the first coefficient, the replacement load, the second coefficient, and the replacement moment when the external load acts on the target member.

Abstract: A joint structure includes a first member having a fit-in groove, a second member made of a material different from a material of the first member and having an insertion section to be inserted into the fit-in groove, and a plurality of bonding layers having different hardness and formed between the fit-in groove and the insertion section.

Abstract: A flight restriction setting system includes a damage detector and a flight restriction calculator. The damage detector is configured to detect damage caused to a structure constituting an aircraft. The flight restriction calculator is configured to set flight restriction on the aircraft according to a degree of the damage detected by the damage detector.

Abstract: An aircraft control system includes a flow control device and a control circuit. The flow control device is configured to control a flow of air around an aircraft. The control circuit is configured to control the flow control device so that a pressure distribution loaded on a surface of a structure that constitutes the aircraft is equal to a control value of a pressure distribution calculated based on a physical quantity detected by a sensor provided in the aircraft. The physical quantity relates to the air.

Abstract: According to one implementation, a damage detection system includes: a physical quantity detection unit, a flight condition changing part and a damage detection part. The physical quantity detection unit detects a physical quantity of a structural object composing an aircraft during a flight of the aircraft. The flight condition changing part changes at least one flight condition of the aircraft to at least one specific flight condition when the physical quantity of the structural object has been detected by the physical quantity detection unit. The damage detection part determines whether a damage arose in the structural object, based on a physical quantity which has been detected, from the structural object of the aircraft flying with the at least one specific flight condition, by the physical quantity detection unit.

Abstract: A joint structure includes a first member having a fit-in groove, a second member made of a material different from a material of the first member and having an insertion section to be inserted into the fit-in groove, and a plurality of bonding layers having different hardness and formed between the fit-in groove and the insertion section.

Abstract: According to one implementation, a damage detection system includes: a physical quantity detection unit, a flight condition changing part and a damage detection part. The physical quantity detection unit detects a physical quantity of a structural object composing an aircraft during a flight of the aircraft. The flight condition changing part changes at least one flight condition of the aircraft to at least one specific flight condition when the physical quantity of the structural object has been detected by the physical quantity detection unit. The damage detection part determines whether a damage arose in the structural object, based on a physical quantity which has been detected, from the structural object of the aircraft flying with the at least one specific flight condition, by the physical quantity detection unit.

Abstract: A load calculator includes a coefficient storage, a replacement deriver, and an internal-load deriver. The storage stores a first coefficient, an internal load acting on a target point in a target member when a unit load acts on a concentrated load point in the target member along one of three orthogonal axes, and as a second coefficient, an internal load acting on the target point when a unit moment acts on the concentrated load point around one of the axes. The replacement deriver derives a replacement load and moment by replacing an external load acting on the target member with six force components acting on the concentrated load point. The internal load deriver derives an internal load acting on any target point with the first coefficient, the replacement load, the second coefficient, and and the replacement moment when the external load acts on the target member.

Abstract: According to one implementation, a damage detection system includes: a physical quantity detection unit, a flight condition changing part and a damage detection part. The physical quantity detection unit detects a physical quantity of a structural object composing an aircraft during a flight of the aircraft. The flight condition changing part changes at least one flight condition of the aircraft to at least one specific flight condition when the physical quantity of the structural object has been detected by the physical quantity detection unit. The damage detection part determines whether a damage arose in the structural object, based on a physical quantity which has been detected, from the structural object of the aircraft flying with the at least one specific flight condition, by the physical quantity detection unit.

Abstract: According to one implementation, a damage detection system includes optical paths, a light source, a photodetector, and a signal processing system, a signal processing system. The optical paths propagate lights in at least three different directions. The optical paths have at least two paths per one direction. The light source makes the lights incident on one ends of the optical paths respectively. The photodetector detects the lights output from other ends of the optical paths. The signal processing system specifies at least one location of damage based on optical detection signals detected by the photodetector.

Abstract: A flight restriction setting system includes a damage detector and a flight restriction calculator. The damage detector is configured to detect damage caused to a structure constituting an aircraft. The flight restriction calculator is configured to set flight restriction on the aircraft according to a degree of the damage detected by the damage detector.

Abstract: According to one implementation, a damage detection system includes optical paths, a light source, a photodetector, and a signal processing system, a signal processing system. The optical paths propagate lights in at least three different directions. The optical paths have at least two paths per one direction. The light source makes the lights incident on one ends of the optical paths respectively. The photodetector detects the lights output from other ends of the optical paths. The signal processing system specifies at least one location of damage based on optical detection signals detected by the photodetector.

Abstract: An aircraft control system includes a flow control device and a control circuit. The flow control device is configured to control a flow of air around an aircraft. The control circuit is configured to control the flow control device so that a pressure distribution loaded on a surface of a structure that constitutes the aircraft is equal to a control value of a pressure distribution calculated based on a physical quantity detected by a sensor provided in the aircraft. The physical quantity relates to the air.

Abstract: According to one implementation, a damage detection system includes: a physical quantity detection unit, a flight condition changing part and a damage detection part. The physical quantity detection unit detects a physical quantity of a structural object composing an aircraft during a flight of the aircraft. The flight condition changing part changes at least one flight condition of the aircraft to at least one specific flight condition when the physical quantity of the structural object has been detected by the physical quantity detection unit. The damage detection part determines whether a damage arose in the structural object, based on a physical quantity which has been detected, from the structural object of the aircraft flying with the at least one specific flight condition, by the physical quantity detection unit.

Abstract: According to one implementation, a composite material structure includes a first member and a second member. The first member has at least one first bonded surface. The second member has at least one second bonded surface to be bonded to the at least one first bonded surface. The second member is made of a composite material. At least one surface formed by fibers forming the composite material is used as the at least one second bonded surface by disposing end portions of the fibers, in the first member side, inside the composite material.

Abstract: According to one implementation, a composite material structure includes a first member and a second member. The first member has at least one first bonded surface. The second member has at least one second bonded surface to be bonded to the at least one first bonded surface. The second member is made of a composite material. At least one surface formed by fibers forming the composite material is used as the at least one second bonded surface by disposing end portions of the fibers, in the first member side, inside the composite material.

Abstract: An on-line system having a plurality of terminal equipments and host computers connectable to the terminal equipments, each host computer responsive to a job request from a terminal equipment being provided with an on-line process for transferring the control of the job request to a job execution process determined in accordance with the content of the job request, and a plurality of regular job execution processes for executing, if the job request is a regular job request, a regular job for the regular job request. The on-line control process is provided with an irregular job execution process space generating process for generating an irregular job execution process space for the irregular job execution.

Abstract: The disclosure is directed to the manufacture of bean curd having a coarse structure. Soybean milk is coagulated and a mass of coagulated soybean milk is broken into smaller lumps. These lumps are distributed into a plurality of continuously moving cups. Fluid soybean milk is poured into each cup to promote coagulation and bonding of its contents as the fluid milk is combined with residual coagulant solution in the cup. The cups are heated, whereby a cake of coarse-grained bean curd is produced in each cup. Disclosed also is an apparatus particularly adapted for carrying out the method.