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公开(公告)号：US09523562B2
公开(公告)日：2016-12-20
申请号：US14672531
申请日：2015-03-30
发明人： Keisuke Ando , Yoshihiko Ueno , Yoshihiro Sera , Shojiro Furuya
摘要： 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.
摘要翻译： 一种飞行器包括外表面，运算单元和控制单元。 算术单元使用控制参数来计算控制命令。 控制单元基于控制命令控制飞行器的姿态或飞行器的推力。 飞行器的外表面的至少一部分由消融材料组成。 运算单元响应于由消融材料消失引起的飞行器的形状变化量来改变控制参数。
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公开(公告)号：US11067036B2
公开(公告)日：2021-07-20
申请号：US15120859
申请日：2015-02-13
发明人： Yoshihiko Ueno , Tasuku Suzuki , Shojiro Furuya
摘要： 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.
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3.发明授权公开(公告)号：US09952022B2
公开(公告)日：2018-04-24
申请号：US14668020
申请日：2015-03-25
发明人： Yoshihiko Ueno , Shojiro Furuya
CPC分类号： F41H7/04 , B64C39/022 , B64C39/024 , B64C2201/027 , B64C2201/08 , B64C2201/122 , B64C2201/146 , B64C2201/148 , B64C2201/208 , B64F1/12 , B64F1/222 , G05D1/0094
摘要： 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.
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公开(公告)号：US10739004B2
公开(公告)日：2020-08-11
申请号：US15123431
申请日：2015-02-18
发明人： Yoshihiko Ueno , Shojiro Furuya
摘要： The jet engine includes an inlet and a combustor. The inlet (11) takes air. The combustor burns fuel with the air. The combustor includes an injector (20). The injector (20) has an opening (31) through which the fuel is injected. The injector (20) includes a self-extinguishing member (32). The self-extinguishing member (32) self-extinguishes with time in a flight so that the injection direction of the fuel is modified.
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公开(公告)号：US10697397B2
公开(公告)日：2020-06-30
申请号：US15121172
申请日：2015-02-13
发明人： Yoshihiko Ueno , Oto Yamamoto , Tasuku Suzuki , Shojiro Furuya
摘要： 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.
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公开(公告)号：US10274199B2
公开(公告)日：2019-04-30
申请号：US15120867
申请日：2015-02-17
发明人： Yoshihiko Ueno , Shojiro Furuya
摘要： A jet engine includes an inlet (11) which takes in air and a combustor (12) which combusts fuel with the air. The combustor (12) has an injector (20), a plurality of flame stabilizers (21, 22) and a vanishment section (31). The injector (20) injects the fuel. The plurality of flame stabilizers (21, 22) can maintain the flame (F) used for combustion in the combustor (12). The vanishment section (31) is provided to cover the dent of the first flame stabilizer (21) which is situated on the side near to the inlet in the plurality of flame stabilizers (21, 22), and vanishes with the passage of time in the flight.
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公开(公告)号：US11248562B2
公开(公告)日：2022-02-15
申请号：US16071980
申请日：2016-06-22
发明人： Mariko Hirokane , Keisuke Ando , Yoshihiko Ueno
摘要： A jet engine has an inlet 11 configured to introduce air, and a combustor 12 having a fuel injection port 30a that injects a fuel, and configured to combust the fuel injected from the fuel injection port 30a by using the air. The combustor 12 has a separation section 14 defining the air passage FA through which the air flows, between a rear end 15 of the inlet and the fuel injection port 30a. A plurality of turbulent flow generating sections (20;25) are arranged in the separation section 14 to makes the air flow turbulent. Each of the plurality of turbulent flow generating sections (20;25) contains a member (21;22;25B) which can restrain the turbulence of the air flow by moving or disappearing. It can be prevented that a high-pressure region reaches the inlet so that the thrust of the jet engine is reduced.
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公开(公告)号：US11203984B2
公开(公告)日：2021-12-21
申请号：US15121187
申请日：2015-02-18
发明人： Yoshihiko Ueno , Shojiro Furuya
IPC分类号： F02C9/00 , F02C9/32 , F02C7/232 , B64D33/02 , F23R3/28 , F02K7/18 , F02C9/44 , F23N1/00 , F02K7/14 , F02C7/04 , F02C7/22 , F02K7/00
摘要： 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.
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公开(公告)号：US10830439B2
公开(公告)日：2020-11-10
申请号：US15121178
申请日：2015-02-17
发明人： Yoshihiko Ueno , Shojiro Furuya
摘要： A jet engine includes an inlet and a combustor. the inlet takes in air. The combustor combusts fuel with the air. The combustor (12) includes an injector (20) having a plurality of openings (31a, 31b) from which the fuel is injected. The plurality of openings (31a, 31b) are arranged in a direction perpendicular to a direction of a flow path of the air in the combustor (12). The plurality of openings (31a, 31b) include two types of openings different in area.
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