Mitsubishi Heavy Industries Limited

Shojiro Furuya

Yoshihiko Ueno

Tasuku Suzuki

Yukito Hata

Mariko Sato

Keisuke Ando

Masaharu Nakamura

Yoshihiro Sera

Takuto Haniu

Mariko Hirokane

Daichi Miyoshi

Shotaro Nako

Tomohisa Wada

Oto Yamamoto

A jet engine is provided which can efficiently pressurize fuel. A jet engineincludes a pumpthat heats fuel, a heating conduitthat heats the pressurized fuel, a fuel turbinethat provides mechanical power to the pump, and an electric rotating machine. When a given condition is not satisfied, the electric rotating machineprovides mechanical power to the fuel turbine. When the given condition is satisfied, the fuel that has passed through the heating conduitbefore combustion flows into the fuel turbineto provide mechanical power to the fuel turbine

Jet engine

A scramjet engine has a first passage forming member and a second passage forming member. A passage is formed between a first surface and a second surface. The passage has an upstream zone, a combustion zone and a downstream zone. A cavity of a concave shape is provided on the first surface in the combustion zone. The first passage forming member has a convex section located in the upstream zone, a first fuel injection section configured to inject fuel into the passage from a first fuel nozzle provided for the convex section, and a second fuel injection section configured to inject fuel to the cavity. The second passage forming member has a third fuel injection section configured to inject fuel to a direction toward the first surface from the second surface in the passage through a second fuel nozzle provided in the downstream zone.

Scramjet engine

A jet engine has an inlet which takes in air, a combustor which combusts fuel by using the air, and a fuel control section which controls supply of the fuel. The combustor has a fuel supplying section which supplies the fuel, injectors which inject the fuel. Each injector contains openings which inject the fuel. The fuel supplying section supplies the fuel to the injector in a flow rate according to a command of an autopilot. The fuel control section controls the injectors such that the number of the openings which inject the fuel or flow-path cross-section areas of the pipes which send the fuel in case of the low-speed is more than the number of the openings which inject the fuel or the flow-path cross-section areas of the pipes which send the fuel in case of the high-speed.

Jet engine, flying object, and method of operating a jet engine

A jet engine includes an inlet that takes air, and a combustor that burns fuel using the air. The combustor includes a fuel injector and an igniter for igniting a gas mixture of the air and the fuel. The igniter ignites and activates automatically by heat and pressure created by compression of the air that has been taken in through the inlet.

Combustor and jet engine having the same

A jet engine includes an inlet and a combustor. the inlet takes in air. The combustor combusts fuel with the air. The combustor () includes an injector () having a plurality of openings () from which the fuel is injected. The plurality of openings () are arranged in a direction perpendicular to a direction of a flow path of the air in the combustor (). The plurality of openings () include two types of openings different in area.

The jet engine includes an inlet and a combustor. The inlet () takes air. The combustor burns fuel with the air. The combustor includes an injector (). The injector () has an opening () through which the fuel is injected. The injector () includes a self-extinguishing member (). The self-extinguishing member () self-extinguishes with time in a flight so that the injection direction of the fuel is modified.

Jet engine, flying object and method of operating jet engine

A combustor of a jet engine includes a fuel injector, an igniter for igniting a gas mixture of air and fuel, and a flame holder. The igniter is disposed in the flame holder. After an activation of the igniter, the igniter disappears, and a space after the disappearance functions as a flame-holding space.

Combustor, jet engine, flying body, and operation method of jet engine

A jet engine includes an inlet () which takes in air and a combustor () which combusts fuel with the air. The combustor () has an injector (), a plurality of flame stabilizers () and a vanishment section (). The injector () injects the fuel. The plurality of flame stabilizers () can maintain the flame (F) used for combustion in the combustor (). The vanishment section () is provided to cover the dent of the first flame stabilizer () which is situated on the side near to the inlet in the plurality of flame stabilizers (), and vanishes with the passage of time in the flight.

Jet engine, flying object, and method of operating jet engine

An armored vehicle includes: a basic armored vehicle having a predetermined basic external armor; a modularized armor structure exchangeably attached to the basic external armor; and an unmanned aerial vehicle loaded on the modularized armor structure. The modularized armor structure includes: an unmanned aerial vehicle loading section configured to load the unmanned aerial vehicle; an armoring material structure formed of armoring material; and an attaching section used to exchangeably attach the modularized armor structure to the basic armored vehicle.

Modularized armor structure with unmanned aerial vehicle loaded and armored vehicle using the same

An optical test apparatus includes a three-dimensional dome, light sources and a control unit. The three-dimensional dome covers a field of view of an image acquisition device. The image acquisition device is a test target device. The light sources are dispersedly arranged on the three-dimensional dome and generate a predetermined image on the three-dimensional dome. The first control unit controls the light sources.

Optical test apparatus

An aerial vehicle includes an outer surface, an arithmetic unit and a control unit. The arithmetic unit calculates a control command using a control parameter. The control unit controls an attitude of the aerial vehicle or a thrust of the aerial vehicle based on the control command. At least a part of the outer surface of the aerial vehicle is composed of ablation material. The arithmetic unit changes the control parameter in response to an amount of shape change of the aerial vehicle caused by disappearance of the ablation material.

Aerial vehicle and operating method of aerial vehicle

An image obtaining apparatus has a swing-type optical system, an optical dome and a correction optical system. The swing-type optical system is configured to adjust a photographing direction based on a swinging operation. The correction optical system corrects transmitted light beams through the optical dome to parallel light beams parallel to the photographing direction.

Growing community of inventors

Tokyo, Japan

Shojiro Furuya