Subaru Corporation

Yukinobu Tomonaga

Satoshi Kuroyanagi

Akitoshi Sakaguchi

Shinichi Harada

Yu Takahashi

Hiroki Kato

Akihiro Yamane

Yoichi Onomura

Maki Kikuchi

Norihiko Adachi

Takayuki Oguri

Takeshi Fukurose

Yasuhiro Yoshifuku

Kohei Nakano

Yohei Matsuguma

According to one implementation, a rotorcraft includes a first rotorcraft and at least one second rotorcraft. The first rotorcraft has a first main rotor and a first tail rotor. The at least one second rotorcraft has a second main rotor and a second tail rotor. The at least one second rotorcraft are attachable and detachable to and from the first rotorcraft. Further, according to one implementation, a method of controlling the above-mentioned rotorcraft includes: flying the first rotorcraft, to which the at least one second rotorcraft has been attached, to a destination; and separating the at least one second rotorcraft from the first rotorcraft at the destination.

Rotorcraft and method of controlling rotorcraft

An aircraft landing assist apparatus includes an image obtaining unit, a shape obtaining unit, a measuring unit, and a calculating unit. The image obtaining unit is configured to obtain an image of a surrounding region of a landing point on which an aircraft is to land. The shape obtaining unit is configured to obtain a shape of the surrounding region of the landing point on the basis of the obtained image. The measuring unit is configured to measure an above-air wind direction and an above-air wind velocity. The calculating unit is configured to calculate a landing-point wind direction and a landing-point wind velocity on the basis of the obtained shape of the surrounding region of the landing point, the measured above-air wind direction, and the measured above-air wind velocity.

Aircraft landing assist apparatus, aircraft landing assist method, and non-transitory storage medium

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 self-position measuring device includes an information generator, a position extractor, and a navigation method selector. The information generator generates estimated information that is expected to be obtained when at least one of the ground information and the celestial information is obtained, at each of multiple reference points generated on the basis of measured inertial navigation position. The position extractor checks at least the one of the ground information and the celestial information against the estimated information at each of the multiple reference points and extracts a position of a specific reference point corresponding to specific estimated information with a highest matching degree. The navigation method selector selects, on the basis of the specific reference point, a navigation method with less navigational error as a navigation method for measuring the self-position.

Self-position measuring device, self-position measuring method, and non-transitory storage medium

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

A flight path setting apparatus includes a display unit, a selector, a range calculator, and a display controller. The display unit displays a flight path of an aircraft. The flight path includes a plurality of points. The selector selects a first point on the basis of an operation performed by a user. The first point is any one of the points displayed by the display unit. The range calculator calculates a non-settable range on the basis of a flight performance and a surrounding environment of the aircraft. The non-settable range is a region that is around the first point and in which a second point is not settable. The second point is subsequent to the first point on the flight path. The display controller causes the display unit to display the non-settable range that relates to the first point and is calculated by the range calculator.

Flight path setting apparatus, flight path setting method, and computer readable medium

A formation setting apparatus includes a display unit, a selector, a region calculator, a display controller, and a communication controller. The display unit displays a formation of formation flying that includes aircrafts. The selector selects, as a first aircraft, one of the aircrafts displayed on the display unit, on a basis of an operation performed by a user. The region calculator calculates a movable region of the first aircraft, on a basis of a distance, to the first aircraft, from one or a plurality of second aircrafts of the aircrafts excluding the first aircraft. The display controller causes the calculated movable region to be displayed on the display unit. The communication controller transmits a control signal to the first aircraft when a position within the movable region displayed on the display unit is selected by the user. The control signal causes the first aircraft to move to the selected position.

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Tokyo, Japan

Yukinobu Tomonaga