Subaru Corporation

Iwao Murata

Kei Suzuki

Yuichi Nagai

Marosuke Kikuchi

Yasunori Shibao

Kazuaki Kotani

Nobuyuki Nakazato

Hiroki Kato

Kohei Takahashi

Kentaro Yoshida

Yoichi Onomura

Eisuke Shimizu

Kousaburou Akiba

Masahito Hayakawa

Kumiko Kindaichi

Kazushige Sato

Keiji Hori

Tsutomu Tomizawa

An aircraft includes a plurality of control targets, avionics devices and a control switch unit. The control targets each includes a power line communication unit configured to perform communication via a power line. The avionics devices are respectively connected with the control targets via exclusive-use signal lines. The avionics devices are configured to control the control targets via the signal lines. The avionics devices each includes a PLC unit configured to perform communication via the power line. The control switch unit is configured to, when an abnormality occurs in any of the avionics devices, cause another one of the avionics devices to control the control target which has been controlled by the any of the avionics devices, via the power line.

Aircraft

According to one implementation, a rotating device includes at least one ring, at least one motor and a power transmission mechanism. The least one ring rotates in a circumference direction. The at least one ring includes no hub for housing a motor inside the at least one ring. The at least one motor generates power for rotating the at least one ring. The power transmission mechanism transmits the power to the at least one ring.

Rotating device and aircraft

An aircraft steering system includes an electric actuator, a clutch, at least one plasma actuator, and a controller. The electric actuator is configured to vary an angle of a flight control surface of an aircraft. The clutch is configured to cut off torque by driving of the electric actuator. The torque is to be transmitted to the flight control surface. The at least one plasma actuator is configured to form a flow of air on a surface of the flight control surface when the torque is cut off. The controller is configured to control the electric actuator, the clutch, and the at least one plasma actuator.

Aircraft steering system, aircraft, and aircraft steering method

A fluid level detection apparatus includes a vibrator, a vibration sensor, and a controller. The vibrator is configured to apply a vibration to a container that contains a fluid. The vibration sensor is configured to detect a vibration wave that is generated by the vibrator and propagates through the container. The controller is configured to control an operation of the vibrator and perform arithmetic processing on a detection signal obtained from the vibration sensor. The vibrator and the vibration sensor are provided on an outer wall surface of the container at respective positions that interpose, from above and below, a fluid level of the fluid provided in the container. The controller is configured to calculate a height of the fluid level, on the basis of the vibration wave detected by the vibration sensor.

Fluid level detection apparatus, fluid level detection method, and computer-readable medium containing fluid level detection program

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.

Landing gear of rotorcraft

A failure diagnostic system includes an instrument and a failure diagnostic device. The instrument makes measurement of a measured value regarding behavior of a diagnosis target. The failure diagnostic device has a model of the diagnostic target and performs simulation based on the model. The failure diagnostic device offers a user a proposal for execution of a special operation on the diagnostic target, on the condition that a difference between a result of the simulation and the measured value is greater than a predetermined error range but the difference provides an insufficient basis to determine whether or not the diagnosis target has a failure. The result of the simulation is calculated with the model supplied with a same input as an input to the diagnosis target at the time of the measurement by the instrument of the measured value regarding the behavior of the diagnosis target.

Failure diagnostic system

According to one implementation, a rotorcraft includes rotors, a fuselage, at least three rods, at least one load sensor and a control device. The rotors obtain lift. The fuselage is coupled to the rotors. The at least three rods support the fuselage. The at least one load sensor detects loads applied on the at least three rods. The control device automatically controls the rotors so that measured values of the loads detected by the at least one load sensor are brought to targeted values of the loads.

Rotorcraft and method of controlling rotorcraft

According to one implementation, a flight support system of an aircraft includes storage and an information processing device. The storage stores position information on at least one river above which a space is an option for a flight path of the at least one aircraft. The information processing device automatically determines at least whether the flight path of the at least one aircraft should be over a specific river included in the at least one river in order to fly the at least one aircraft to a destination, based on the position information stored in the storage.

Flight support system of aircraft, method of supporting flight of aircraft, flight support medium of aircraft, and aircraft

A position measurement system includes a movable body and at least one indicator including identification information. The movable body includes an optical sensor configured to acquire an image of the indicator, an information acquisition unit configured to acquire the identification information of the indicator and a bearing of the indicator as seen from the movable body based on the image of the indicator acquired by the optical sensor, a coordinate acquisition unit configured to acquire coordinates of the indicator based on the acquired identification information of the indicator, and a position calculation unit configured to calculate a position of the movable body based on the acquired bearing of the indicator and the acquired coordinates of the indicator. The indicator includes, as the identification information, at least one of a unique reflection spectrum, a spectrum change pattern, a hue change pattern, a brightness change pattern, or a temperature change pattern.

Position measurement system for movable body

An image projection apparatus includes: a projector; a projection control apparatus; and a color tone sensor. The projector projects an image. The projection control apparatus causes the projector to perform a projection on a surface of a target serving as a projection target. The color tone sensor detects a color tone of the surface of the target on which an image is projected. The projection control apparatus adjusts a color tone of an image to be projected on a basis of a detection result of the color tone sensor such that the color tone detected by the color tone sensor has a predetermined value.

Image projection apparatus

An image projection apparatus includes: a projector; and a projection control apparatus. The projector projects an image. The projection control apparatus causes the projector to project a processing information regarding a processing or an assembly information regarding an assembly performed for a target to be manufactured on a surface of the target.

There is provided a supercharging system for an aircraft reciprocating engine, comprising: a plurality of compressors for supplying compressed air to the aircraft reciprocating engine; at least one turbine for obtaining rotational power for at least one of the plurality of compressors, and a plurality of motors for respectively providing rotational power to the plurality of compressors. An object of the present invention is to reduce turbo lag in a reciprocating engine for an aircraft in which multiple-stage supercharging is performed by the turbocharger.

Supercharging system for aircraft reciprocating engine, aircraft reciprocating engine, and aircraft

A manufacturing assistance apparatus includes a display, an imaging device, a completion determining unit, and a display controller. The display is configured to display operation information that is related to any of operation processes of a workpiece. The imaging device is configured to perform imaging of the workpiece, and output image data obtained by the imaging. The completion determining unit is configured to determine whether current one of the operation processes is completed, on a basis of the image data outputted from the imaging device. The display controller is configured to cause, when the current one of the operation processes is determined by the completion determining unit as being completed, the display to display the operation information that is related to subsequent one of the operation processes.

Manufacturing assistance apparatus

An image projection apparatus includes: a projector; and a projection control apparatus. The projector projects an image. The projection control apparatus causes the projector to project an information indicating a border of a painting applied to a surface of a target to be manufactured on the surface of the target.

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Tokyo, Japan

Iwao Murata