Subaru Corporation

Masakatsu Abe

Kensuke Yoshimura

Hiroki Kato

Naoyuki Sekine

Hideki Soejima

Takeshi Fukurose

Takuya Nakano

Takashi Miyawaki

Yoshikazu Kosugi

Yuichiro Yasunaga

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.

Flight control device for aircraft

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.

Joint structure

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.

Flight restriction setting system, flight restriction setting method, and non-transitory storage medium

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.

Aircraft control system, aircraft control method, and aircraft

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.

In-flight damage detection system and damage detection method

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.

Damage detection system and damage detection method

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.

Growing community of inventors

Tokyo, Japan

Masakatsu Abe