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公开(公告)号：CN105882954A
公开(公告)日：2016-08-24
申请号：CN201610350995.3
申请日：2016-05-25
Applicant: 沈阳航空航天大学
CPC classification number: B64C27/08 , B64C27/12 , B64C2201/024 , B64C2201/04 , B64D35/02
Abstract: 一种带有四个辅助翼的混合动力无人机及其控制方法。本发明综合直升机与四旋翼的优势，综合油动与电动的优势，设计了一款以直升机架构为主体，以四旋翼架构为辅助的油、电混合动力系统的垂直起降无人机。此架构无人机包括主旋翼、垂直尾翼、左前辅助旋翼、右前辅助旋翼、左后辅助旋翼和右后辅助旋翼，共六个旋翼。无人机整体上采用直升机的基本架构，但将传统的直升机主旋翼的浆距可调浆叶换为普通的固定浆距浆叶，此种变动虽然使主旋翼失去了控制飞行方向的功能，但却有效降低了制造成本。而无人机飞行方向和机动动作的控制，则由垂直尾翼和四个辅助旋翼完成。本发明的主旋翼采用内燃机为动力，以增强无人机的续航能力，其他旋翼采用无刷电机为动力，以提高无人机的稳定性和机动性。
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公开(公告)号：US20180016022A1
公开(公告)日：2018-01-18
申请号：US15523244
申请日：2015-10-28
Applicant: ACC Innovation AB
Inventor： Anders Ljung
CPC classification number: B64D35/04 , A63H27/12 , B64C39/024 , B64C2201/027 , B64C2201/04 , B64C2201/06 , B64C2201/108 , B64C2201/146 , B64C2201/148 , B64D37/00
Abstract: Multi-rotor aerial vehicle (1, 1′, 1″, 1′″, 1″″, 1″″′, 1″″″) comprising, at least a first, second and third rotor 10, 20, 30, each rotatable by a dedicated first second and third hydraulic motor 11, 21, 31, a power unit 2, at least a first, second and third hydraulic pump 12, 22, 32 dedicated to the respective first, second and third hydraulic motor 11, 21, 31, wherein each hydraulic pump 12, 22, 32 is arranged to provide pressurized fluid to each hydraulic motor 11, 21, 31 for powering the hydraulic motor 11, 21, 31 and thereby rotating the respective rotor 10, 20, 30, a control unit 6 for controlling the operation of the multi-rotor aerial vehicle (1, 1′, 1″, 1′″, 1″″, 1″″′, 1″″″), wherein the control of the multi-rotor aerial vehicle (1, 1′, 1″, 1′″, 1″″, 1″″′, 1″″″) is arranged to be performed by altering the flow of pressurized fluid distributed to each respective hydraulic motor 11, 21, 31, wherein, wherein the flow of pressurized fluid provided to each hydraulic motor 11, 21, 31 is individually controllable by means of at least one control valve 13, 23, 33 configured to control the flow of pressurized fluid from each hydraulic pump 12, 22, 32 to its dedicated hydraulic motor 11, 21, 31.
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公开(公告)号：US20160090184A1
公开(公告)日：2016-03-31
申请号：US14867152
申请日：2015-09-28
Applicant: REEBEEZ, INC
Inventor： Ankita Ghoshal
CPC classification number: B64D27/24 , B60L8/003 , B64C39/024 , B64C2201/04 , B64C2201/042 , B64D2027/026 , H01L35/00 , H01L35/04 , H01L35/12 , H01L35/22 , H01L35/28 , H01L35/30 , H01L35/32 , H01L35/34 , H02P31/00 , H02P2201/07 , H02S10/30 , Y02T10/7083 , Y02T50/64
Abstract: This disclosure generally relates to a hybrid solid-state propulsion system for aerial vehicles. The hybrid propulsion system includes a combustor, a thermophotovoltaic generator, and a thermoelectric generator. The combustor burns a chemical based fuel to produce radiation and heat that are converted into electricity used to power the aerial vehicle. The thermophotovoltaic generator is positioned to receive radiation and remnant heat generated by flames in the combustor while the thermoelectric generator receives heat from exhausted flue gases from the combustor.
Abstract translation: 本公开一般涉及用于空中飞行器的混合固态推进系统。 混合推进系统包括燃烧器，热光伏发电机和热电发电机。 燃烧器燃烧基于化学物质的燃料以产生被转换成用于为飞行器运行的电力的辐射和热量。 热光电发生器被定位成接收由燃烧器中的火焰产生的辐射和残余热，同时热电发电机从来自燃烧器的排出的废气中接收热量。
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公开(公告)号：US20230192287A1
公开(公告)日：2023-06-22
申请号：US17558307
申请日：2021-12-21
Applicant: Bell Textron Inc.
Inventor： Steven R. Ivans , Berlin B. Benfield
CPC classification number: B64C29/0033 , B64C39/024 , B64C1/1415 , B64C2201/088 , B64C2201/04 , B64C2201/024
Abstract: There is disclosed in one example an unmanned vertical lift aircraft, comprising: an airframe; a drive system configured for vertical takeoff and landing (VTOL); a power plant to power the drive system; and an internal cargo bay comprising a fore aperture and an aft aperture, the fore and aft apertures having dimensions substantially conforming to a cross section of the internal cargo bay, and the internal cargo bay comprising a substantially linear and open volume between the fore and aft apertures.
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公开(公告)号：US20180093755A1
公开(公告)日：2018-04-05
申请号：US15689945
申请日：2017-08-29
Applicant: AeroVironment, Inc.
Inventor： Carlos Thomas Miralles
CPC classification number: B64C13/16 , B64B2201/00 , B64C39/024 , B64C2201/04 , B64C2201/121 , B64C2201/141 , B64C2201/165 , F41G7/2253 , F41G7/2286 , F41G7/2293 , G05D1/12
Abstract: A system comprising an unmanned aerial vehicle (UAV) having wing elements and tail elements configured to roll to angularly orient the UAV by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor a boresight angle error correction value bases on distance between a target point and a boresight point of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point to a re-oriented target point in the body-fixed frame, to maintain the offset angle via the offset angle correction value.
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Patent Agency Ranking
公开(公告)号：EP3172435A1
公开(公告)日：2017-05-31
申请号：EP15759845.9
申请日：2015-07-15
Applicant: Institut Polytechnique de Grenoble
Inventor： LOZANO, Rogelio
CPC classification number: F03D9/32 , A63H27/08 , B63H9/0685 , B64C31/06 , B64C39/022 , B64C39/024 , B64C2201/04 , B64C2201/107 , F03D5/00 , F03D9/00 , F03D9/25 , F03D13/20 , Y02E10/70 , Y02E10/728
Abstract: The invention concerns an airborne device (10) comprising at least three supporting wings (12) and a linking device (18), the wings being linked to each other by first flexible cables (16), each wing being further linked to the linking device (18) by a second flexible cable (20), the linking device being linked to a third flexible cable (22) intended to be linked to a base (46, 48), the first, second and third cables being tensioned when the airborne device is carried in the wind.
Abstract translation: 本发明涉及包括至少三个支撑翼（12）和连接装置（18）的机载装置（10），这些翼通过第一柔性缆线（16）彼此连接，每个翼还连接到连接装置 通过第二柔性缆线（20）连接到所述第一缆线（18），所述链接装置链接到旨在连接到基部（46,48）的第三柔性缆线（22），所述第一缆线，第二缆线和第三缆线在空中 装置在风中携带。
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公开(公告)号：EP3212502A1
公开(公告)日：2017-09-06
申请号：EP15854629.1
申请日：2015-10-28
Applicant: ACC Innovation AB
Inventor： LJUNG, Anders
CPC classification number: B64D35/04 , A63H27/12 , B64C39/024 , B64C2201/027 , B64C2201/04 , B64C2201/06 , B64C2201/108 , B64C2201/146 , B64C2201/148 , B64D37/00
Abstract: Multi-rotor aerial vehicle (1, 1′, 1″, 1′″, 1″″, 1″″′, 1″″″) comprising, at least a first, second and third rotor 10, 20, 30, each rotatable by a dedicated first second and third hydraulic motor 11, 21, 31, a power unit 2, at least a first, second and third hydraulic pump 12, 22, 32 dedicated to the respective first, second and third hydraulic motor 11, 21, 31, wherein each hydraulic pump 12, 22, 32 is arranged to provide pressurized fluid to each hydraulic motor 11, 21, 31 for powering the hydraulic motor 11, 21, 31 and thereby rotating the respective rotor 10, 20, 30, a control unit 6 for controlling the operation of the multi-rotor aerial vehicle (1, 1′, 1″, 1′″, 1″″, 1″″′, 1″″″), wherein the control of the multi-rotor aerial vehicle (1, 1′, 1″, 1′″, 1″″, 1″″′, 1″″″) is arranged to be performed by altering the flow of pressurized fluid distributed to each respective hydraulic motor 11, 21, 31, wherein, wherein the flow of pressurized fluid provided to each hydraulic motor 11, 21, 31 is individually controllable by means of at least one control valve 13, 23, 33 configured to control the flow of pressurized fluid from each hydraulic pump 12, 22, 32 to its dedicated hydraulic motor 11, 21, 31.
Abstract translation: 多旋翼飞行器（1,1'，1“，1”'，1“'，1”'，1“'）包括至少第一，第二和 第三转子10,20,30，每个转子通过专用的第一第二和第三液压马达11,21,31，动力单元2，至少第一，第二和第三液压泵12,22,32可旋转，所述第一，第二和第三液压泵12,22,32专用于相应的第一， 第二和第三液压马达11,21,31，其中每个液压泵12,22,32被布置成向每个液压马达11,21,31提供加压流体，用于给液压马达11,21,31供能并由此旋转相应的 转子10,20,30，用于控制多旋翼飞行器（1,1'，1“，1”'，1“，1”''）的操作的控制单元6， 其中多旋翼飞行器（1,1'，1“，1”'，1“'，1”'，1“ ）被布置成通过改变分配给每个相应液压马达11,21,31的加压流体的流动来执行，其中，向每个液压马达提供加压流体的流动 液压马达11,21,31可通过至少一个控制阀13,23,33单独控制，所述至少一个控制阀13,23,33构造成控制从每个液压泵12,22,32到其专用液压马达11,21,31的加压流体的流动 。
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公开(公告)号：EP3212502A4
公开(公告)日：2018-04-04
申请号：EP15854629
申请日：2015-10-28
Applicant: ACC INNOVATION AB
Inventor： LJUNG ANDERS
CPC classification number: B64D35/04 , A63H27/12 , B64C39/024 , B64C2201/027 , B64C2201/04 , B64C2201/06 , B64C2201/108 , B64C2201/146 , B64C2201/148 , B64D37/00
Abstract: Multi-rotor aerial vehicle (1, 1′, 1″, 1′″, 1″″, 1″″′, 1″″″) comprising, at least a first, second and third rotor 10, 20, 30, each rotatable by a dedicated first second and third hydraulic motor 11, 21, 31, a power unit 2, at least a first, second and third hydraulic pump 12, 22, 32 dedicated to the respective first, second and third hydraulic motor 11, 21, 31, wherein each hydraulic pump 12, 22, 32 is arranged to provide pressurized fluid to each hydraulic motor 11, 21, 31 for powering the hydraulic motor 11, 21, 31 and thereby rotating the respective rotor 10, 20, 30, a control unit 6 for controlling the operation of the multi-rotor aerial vehicle (1, 1′, 1″, 1′″, 1″″, 1″″′, 1″″″), wherein the control of the multi-rotor aerial vehicle (1, 1′, 1″, 1′″, 1″″, 1″″′, 1″″″) is arranged to be performed by altering the flow of pressurized fluid distributed to each respective hydraulic motor 11, 21, 31, wherein, wherein the flow of pressurized fluid provided to each hydraulic motor 11, 21, 31 is individually controllable by means of at least one control valve 13, 23, 33 configured to control the flow of pressurized fluid from each hydraulic pump 12, 22, 32 to its dedicated hydraulic motor 11, 21, 31.
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公开(公告)号：US09776709B2
公开(公告)日：2017-10-03
申请号：US14947871
申请日：2015-11-20
Applicant: AeroVironment, Inc.
Inventor： Carlos Thomas Miralles
IPC: G01C23/00 , G05D1/00 , G05D3/00 , G06F7/00 , G06F17/00 , B64C13/16 , G05D1/12 , F41G7/22 , B64C39/02
CPC classification number: B64C13/16 , B64B2201/00 , B64C39/024 , B64C2201/04 , B64C2201/121 , B64C2201/141 , B64C2201/165 , F41G7/2253 , F41G7/2286 , F41G7/2293 , G05D1/12
Abstract: A system comprising an unmanned aerial vehicle (UAV) having wing elements and tail elements configured to roll to angularly orient the UAV by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor a boresight angle error correction value bases on distance between a target point and a boresight point of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point to a re-oriented target point in the body-fixed frame, to maintain the offset angle via the offset angle correction value.
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公开(公告)号：US09688397B2
公开(公告)日：2017-06-27
申请号：US15204547
申请日：2016-07-07
Applicant: Frick A. Smith
Inventor： Frick A. Smith
IPC: B64D35/04 , B64D27/02 , B64C27/22 , B64C29/00 , B64C1/14 , B64C27/52 , B64C39/02 , B64D17/24 , B64D17/34 , B64D17/62 , B64D17/80 , B64D31/00 , B64C27/26 , B64C27/28 , B64C27/82 , B64D17/64
CPC classification number: B64C29/0033 , B64C1/1415 , B64C1/1476 , B64C27/22 , B64C27/26 , B64C27/28 , B64C27/52 , B64C27/82 , B64C29/00 , B64C29/0016 , B64C39/02 , B64C39/024 , B64C2201/04 , B64C2201/088 , B64C2201/10 , B64C2201/104 , B64C2201/108 , B64C2201/162 , B64D17/24 , B64D17/34 , B64D17/62 , B64D17/64 , B64D17/80 , B64D27/02 , B64D31/00 , B64D35/04
Abstract: An aircraft may have a fuselage, a left wing extending from the fuselage, a right wing extending from the fuselage, a tail section extending from a rear portion of the fuselage, and a first engine and a second engine operably connected by a common driveshaft, wherein the first and second engines are configured for freewheeling such that if one of the first and second engines loses power the other of the first and second engines continues to power the aircraft.
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