公开(公告)号：US20190170656A1

公开(公告)日：2019-06-06

申请号：US16257550

申请日：2019-01-25

Applicant: SUBARU CORPORATION

Inventor： Masakatsu ABE

IPC: G01N21/88

CPC classification number: G01N21/8806 ,  G01B11/00 ,  G01N2021/8845 ,  G01N2201/088

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.

公开(公告)号：US20190127051A1

公开(公告)日：2019-05-02

申请号：US16149801

申请日：2018-10-02

Applicant: SUBARU CORPORATION

Inventor： Takashi MIYAWAKI ,  Masakatsu ABE ,  Hiroki KATO

IPC: B64C23/00 ,  B64D45/00 ,  G01N29/04 ,  F15D1/00

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.

公开(公告)号：US20190112072A1

公开(公告)日：2019-04-18

申请号：US16218097

申请日：2018-12-12

Applicant: SUBARU CORPORATION

Inventor： Masakatsu ABE ,  Hideki SOEJIMA ,  Takeshi FUKUROSE

IPC: B64D45/00 ,  G01B17/04 ,  G01N29/04

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.

公开(公告)号：US20200224687A1

公开(公告)日：2020-07-16

申请号：US16688822

申请日：2019-11-19

Applicant: SUBARU CORPORATION

Inventor： Kensuke YOSHIMURA ,  Naoyuki SEKINE ,  Masakatsu ABE

IPC: F16B4/00

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.

公开(公告)号：US20190287322A1

公开(公告)日：2019-09-19

申请号：US16246266

申请日：2019-01-11

Applicant: SUBARU CORPORATION

Inventor： Kensuke YOSHIMURA ,  Masakatsu ABE

IPC: G07C5/08 ,  B64D45/00

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.