公开(公告)号：US20180016022A1

公开(公告)日：2018-01-18

申请号：US15523244

申请日：2015-10-28

申请人： ACC Innovation AB

发明人： Anders Ljung

IPC分类号： B64D35/04 ,  B64D37/00 ,  B64C39/02

CPC分类号： B64D35/04 ,  A63H27/12 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/04 ,  B64C2201/06 ,  B64C2201/108 ,  B64C2201/146 ,  B64C2201/148 ,  B64D37/00

摘要： 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.

公开(公告)号：US20160090184A1

公开(公告)日：2016-03-31

申请号：US14867152

申请日：2015-09-28

申请人： REEBEEZ, INC

发明人： Ankita Ghoshal

IPC分类号： B64D27/24 ,  H02P31/00 ,  H02S10/30 ,  B64C39/02 ,  H01L35/30

CPC分类号： 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

摘要： 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.

摘要翻译： 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。

公开(公告)号：US20230192287A1

公开(公告)日：2023-06-22

申请号：US17558307

申请日：2021-12-21

申请人： Bell Textron Inc.

发明人： Steven R. Ivans ,  Berlin B. Benfield

IPC分类号： B64C29/00 ,  B64C39/02 ,  B64C1/14

CPC分类号： B64C29/0033 ,  B64C39/024 ,  B64C1/1415 ,  B64C2201/088 ,  B64C2201/04 ,  B64C2201/024

摘要： 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.

公开(公告)号：US20180093755A1

公开(公告)日：2018-04-05

申请号：US15689945

申请日：2017-08-29

申请人： AeroVironment, Inc.

发明人： Carlos Thomas Miralles

IPC分类号： B64C13/16 ,  F41G7/22 ,  G05D1/12 ,  B64C39/02

CPC分类号： B64C13/16 ,  B64B2201/00 ,  B64C39/024 ,  B64C2201/04 ,  B64C2201/121 ,  B64C2201/141 ,  B64C2201/165 ,  F41G7/2253 ,  F41G7/2286 ,  F41G7/2293 ,  G05D1/12

摘要： 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.

公开(公告)号：US09776709B2

公开(公告)日：2017-10-03

申请号：US14947871

申请日：2015-11-20

申请人： AeroVironment, Inc.

发明人： Carlos Thomas Miralles

IPC分类号： G01C23/00 ,  G05D1/00 ,  G05D3/00 ,  G06F7/00 ,  G06F17/00 ,  B64C13/16 ,  G05D1/12 ,  F41G7/22 ,  B64C39/02

CPC分类号： B64C13/16 ,  B64B2201/00 ,  B64C39/024 ,  B64C2201/04 ,  B64C2201/121 ,  B64C2201/141 ,  B64C2201/165 ,  F41G7/2253 ,  F41G7/2286 ,  F41G7/2293 ,  G05D1/12

摘要： 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.

公开(公告)号：US09688397B2

公开(公告)日：2017-06-27

申请号：US15204547

申请日：2016-07-07

申请人： Frick A. Smith

发明人： Frick A. Smith

IPC分类号： 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分类号： 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

摘要： 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.

公开(公告)号：US20140367509A1

公开(公告)日：2014-12-18

申请号：US14251850

申请日：2014-04-14

申请人： Frick A. Smith

发明人： Frick A. Smith

IPC分类号： B64C27/22 ,  B64C29/00 ,  B64C27/52 ,  B64C39/02 ,  B64D17/34 ,  B64C1/14 ,  B64D17/80 ,  B64D17/62 ,  B64D17/24 ,  B64D27/02 ,  B64D31/00

CPC分类号： 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

摘要： 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.

摘要翻译： 飞机可以具有机身，从机身延伸的左翼，从机身延伸的右翼，从机身的后部延伸的尾部，以及通过共同的驱动轴可操作地连接的第一发动机和第二发动机， 其中所述第一和第二发动机被配置为自由转动，使得如果所述第一和第二发动机中的一个发动机失去动力，则所述第一和第二发动机中的另一个继续为所述飞行器供电。

公开(公告)号：US20140172200A1

公开(公告)日：2014-06-19

申请号：US14016602

申请日：2013-09-03

申请人： AEROVIRONMENT, INC.

发明人： Carlos Miralles

IPC分类号： B64C13/16

CPC分类号： B64C13/16 ,  B64B2201/00 ,  B64C39/024 ,  B64C2201/04 ,  B64C2201/121 ,  B64C2201/141 ,  B64C2201/165 ,  F41G7/2253 ,  F41G7/2286 ,  F41G7/2293 ,  G05D1/12

摘要： 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.

摘要翻译： 一种包括具有翼元件和尾部元件的无人飞行器（UAV）的系统，其被配置成滚动以通过滚动来成角度地定向UAV，以便在其后期终点阶段将UAV的纵向平面与目标对准。 一种UAV身体重定向的方法，包括：（a）由处理器确定基于身体固定框架的目标点和视轴之间的距离的视轴角度误差校正值; 和（b）实现UAV机动，其包括将目标点平移到身体固定框架中的重定向目标点的角度角色率分量，以经由偏移角度校正值来保持偏移角度。

公开(公告)号：US08720814B2

公开(公告)日：2014-05-13

申请号：US13442544

申请日：2012-04-09

申请人： Frick A. Smith

发明人： Frick A. Smith

IPC分类号： B64C37/00 ,  B64C27/26 ,  B64C27/28

CPC分类号： 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

摘要： 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.

摘要翻译： 飞机可以具有机身，从机身延伸的左翼，从机身延伸的右翼，从机身的后部延伸的尾部，以及通过共同的驱动轴可操作地连接的第一发动机和第二发动机， 其中所述第一和第二发动机被配置为自由转动，使得如果所述第一和第二发动机中的一个发动机失去动力，则所述第一和第二发动机中的另一个继续为所述飞行器供电。

公开(公告)号：US20190186418A1

公开(公告)日：2019-06-20

申请号：US16326717

申请日：2017-08-28

申请人： Bingham Robert A.

发明人： Orlorunfemi Jacob Azundah

IPC分类号： F02K5/00 ,  B64D27/24 ,  B64D27/16

CPC分类号： F02K5/00 ,  B64C2201/04 ,  B64D27/16 ,  B64D27/24 ,  B64D2027/026 ,  F02C7/36 ,  F02K3/06 ,  F05D2260/4031

摘要： A multi-hybrid aircraft engine that includes a primary compressor 1, a multiplier 199 comprising a drive block, a driven block, driven block pistons 54, and primary shafts 78 and 41; an output shaft 105, and a speed regulator 167. The multi-hybrid aircraft engine is configured such that the primary compressor 1 is fluidly connected to the drive block 46 which is mechanically connected to the driven block 57. The primary compressor 1 pumps compressible fluid to the drive block 46 through the speed regulator 167 to drive the drive block 46, which in turn, drives the primary shafts 78 and 41. The primary shafts 78 and 41 drive the driven block 57, which pumps fluid via the driven block pistons 54, to the drive block 46 through the speed regulator 167 to increase the flow rate of compressible fluid within the multi-hybrid aircraft engine. Furthermore, the driven block 57 provides a shaft 68 that is connected to sets of planetary gears 62 connected to an output shaft 105 that drives a propeller 186.