Subaru Corporation

Fuji Jukogyo Kabushiki Kaisha

Toto Ltd.

Akitoshi Sakaguchi

Akihiro Yamane

Yoichi Onomura

Kumiko Kindaichi

Yutaka Sasaki

Hiroki Kato

Hiroshi Tsuboi

Masayuki Nagaishi

Toshiyuki Narahashi

Yukinobu Tomonaga

Masahiro Yamamoto

Shinei Takahashi

Maki Kikuchi

Satoko Kizuka

Akemi Takeshita

Takayuki Oguri

Yu Takahashi

Koji Sonoda

Yu Itabashi

Kentaro Hiraki

Kenshi Miyata

Hidenori Oka

Kohei Nakano

Yasuhiro Yoshifuku

Kentaro Kudo

An aircraft includes a vessel checker, an image generator, an appearance determining unit, and an information transmitter. The vessel checker identifies a suspicious vessel candidate by comparing a marine vessel detected by a marine search radar with a marine vessel transmitting data with an automatic identification system. The image generator generates an image by photographing the suspicious vessel candidate after the aircraft approaches the suspicious vessel candidate in accordance with a route for approaching the suspicious vessel candidate. The appearance determining unit determines whether the suspicious vessel candidate in the image has an appearance characteristic of a suspicious vessel. The information transmitter transmits, to an external apparatus, information indicating that the suspicious vessel candidate has the appearance characteristic of the suspicious vessel if the suspicious vessel candidate has the appearance characteristic of the suspicious vessel.

Aircraft for identifying a suspicious vessel

An aircraft includes an airframe, a hollow member, and a plasma actuator. The hollow member has a body and an internal flow passage. The body extends from front of the airframe to rear of the airframe and has a hollow shape. The internal flow passage extends in the body from the front to the rear. The body has an introduction port configured to introduce a fluid into the internal flow passage, and a blow hole provided more toward the rear than the introduction port, and penetrating the body from an inner circumferential surface of the body to an outer circumferential surface of the body. The plasma actuator is provided at the outer circumferential surface of the body, and disposed on one or more sides, in a circumferential direction of the body, of the blow hole.

Aircraft

A deceiving signal detection system includes a first antenna, a second antenna, and a signal processor. The first antenna is configured to receive at least four radio wave signals. The signal processor determines that the radio wave signals are the deceiving signals by determining that a relative positional relation between the first antenna and the second antenna calculated on a basis of the radio wave signals deviates from an actual relative positional relation between the first antenna and the second antenna by more than a predetermined amount, and also determines whether an orientation of the aircraft determined based on positions of the first antenna and the second antenna matches an orientation of the aircraft calculated based on an inertial navigation system.

Deceiving signal detection system and deceiving signal detection method

A navigation system includes a receiver and a signal processor. The receiver is mounted on a second aircraft. The second aircraft is an acquisition target of location information. The receiver is configured to receive a navigation signal from each of three or more first aircrafts. The navigation signal includes the location information on a location of the corresponding first aircraft. The navigation signal is transmitted as a radio signal from a navigation apparatus mounted on each of the three or more first aircrafts. The signal processor is mounted on the second aircraft. The signal processor is configured to calculate a location of the second aircraft on the basis of the navigation signal.

Navigation system, navigation method, and aircraft

There is provided a navigation system, comprising: a buoy on a water surface movably anchored to a bottom; a plurality of at least three transmitters fixed to the bottom or at different positions in the water for transmitting signals to specify the positions; a receiver, being disposed with the buoy, configured to receive signals transmitted by the plurality of transmitters; a signal processor, being disposed with the buoy, configured to specify the position of the buoy, based on the signals received by the receiver, and generate a navigation signal indicating the position of the buoy, and a radio, being disposed with the buoy, configured to transmit the navigation signal generated in the signal processor wirelessly, the navigation signal being receivable by a radio in a mobile body.

Navigation system and navigation method

A position measuring apparatus includes an imaging device and a controller, and is mounted on one or more mobile objects and configured to measure a position of a target. The imaging device is configured to acquire images of the target from a plurality of locations that are different from each other. The controller is configured to measure, on the basis of the images of the target, one or both of orientations of the target as viewed from the respective locations and distances to the target from the respective locations, correct one of the measured orientations of the target and the measured distances to the target to thereby reduce a difference between times at which the respective images are acquired at the respective locations, and calculate an estimated position of the target, on a basis of one of the corrected orientations of the target and the corrected distances to the target.

Position measuring method, position measuring apparatus, and position measuring system

A flight controlling apparatus includes an information acquiring unit, a point searching unit, a determining unit, and a route changing unit. The information acquiring unit acquires location information of a factor on a ground that possibly influences safety of an aircraft in landing. The point searching unit searches for one or more landing candidate points to prepare for an expected abnormality in the aircraft in flight, on the basis of the location information. The determining unit determines whether the one or more landing candidate points are selected to prepare for the expected abnormality. The route changing unit changes a flight route of the aircraft to cause the one or more landing candidate points to be obtained to prepare for the expected abnormality in a case where the determining unit determines that no landing candidate point is selected to prepare for the expected abnormality.

Flight controlling apparatus, flight controlling method, and non-transitory storage medium

Provided is an operation control apparatus of a movable body that carries out a task at a destination. The operation control apparatus includes a memory, an information acquiring unit, a cell dividing unit, a calculating unit, a determining unit, and a destination changing unit. The cell dividing unit divides map information into multiple cells that include a first cell including the destination, and a second cell. The calculating unit calculates an evaluation value related to a degree to which the task is impeded, of each of the multiple cells. The determining unit determines whether the evaluation value of the first cell is higher than a threshold. The evaluation value determined as higher, the destination changing unit changes the destination to a location in the second cell, the evaluation value of which is equal to or lower than the threshold and is minimal.

Operation control apparatus of movable body, method of controlling operation of movable body, and computer readable medium

A stereo distance measuring apparatus includes a first optical camera and a second optical camera, a position-posture calculator, an image corrector, and a stereo distance measuring unit. The first and second optical cameras are provided in an elastic structure part of an aircraft and separated from each other. The first and second optical cameras constitute a stereo camera. The position-posture calculator calculates, on the basis of a displacement amount of the elastic structure part, first and second position-posture information regarding positions and postures of the first and second optical cameras, respectively. The image corrector generates first and second corrected images by correcting, on the basis of the first and second position-posture information, positions and orientations of images taken by the first and second optical cameras, respectively. The stereo distance measuring unit calculates a distance to a photographing target, on the basis of the first and second corrected images.

Stereo distance measuring apparatus, stereo distance measuring method, and computer readable medium

A flight control system controls flight of an unmanned aerial vehicle by control signals of the unmanned aerial vehicle itself and from a ground facility. The unmanned aerial vehicle and the ground facility are each provided with at least one flight control unit (FCU) capable of controlling driving of an airframe actuator based on a sensor output signal from an airframe sensor. The at least one FCU on the unmanned aerial vehicle and the at least one FCU of the ground facility constitute a redundant system for flight control function. In the redundant system one of the at least one FCU on the unmanned aerial vehicle serves as a main unit. In the case where a malfunction has occurred in an FCU that performs flight control on the unmanned aerial vehicle, the ground facility is capable of causing another FCU to take over flight control function from the FCU.

Growing community of inventors

Tokyo, Japan

Akitoshi Sakaguchi