WO2017012515A1 - 飞行器 - Google Patents
飞行器 Download PDFInfo
- Publication number
- WO2017012515A1 WO2017012515A1 PCT/CN2016/090193 CN2016090193W WO2017012515A1 WO 2017012515 A1 WO2017012515 A1 WO 2017012515A1 CN 2016090193 W CN2016090193 W CN 2016090193W WO 2017012515 A1 WO2017012515 A1 WO 2017012515A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- aircraft
- duct
- frame
- disposed
- propeller
- Prior art date
Links
- 230000007246 mechanism Effects 0.000 claims abstract description 29
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 10
- 230000035939 shock Effects 0.000 claims description 7
- 238000013016 damping Methods 0.000 claims description 2
- 239000000872 buffer Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000002265 prevention Effects 0.000 description 2
- 230000001681 protective effect Effects 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/001—Shrouded propellers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/04—Arrangement or disposition on aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0025—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being fixed relative to the fuselage
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
- B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
- B64D47/08—Arrangements of cameras
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
- B64U30/26—Ducted or shrouded rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C2025/325—Alighting gear characterised by elements which contact the ground or similar surface specially adapted for helicopters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B64U10/13—Flying platforms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
Definitions
- the elastic member is a rubber ball.
- Fig. 10 is a schematic side view showing the structure of the aircraft of the second embodiment.
- FIG. 13 is a schematic structural view of a main control board of Embodiment 2.
- connection In the description of the present invention, it should be noted that the terms “installation”, “connected”, and “connected” are to be understood broadly, and may be fixed or detachable, for example, unless otherwise explicitly defined and defined. Connected, or integrally connected; can be mechanical or electrical; can be directly connected, or indirectly connected through an intermediate medium, can be the internal communication of the two components.
- Connected, or integrally connected can be mechanical or electrical; can be directly connected, or indirectly connected through an intermediate medium, can be the internal communication of the two components.
- the specific meaning of the above terms in the present invention can be understood in a specific case by those skilled in the art.
- the frame 1 is the main frame of the aircraft, and provides a mounting platform for each part of the aircraft. Therefore, any member capable of performing the above functions can be provided as the embodiment.
- Rack 1; the number of propellers 2 may be one or more, for example: three or four, etc.; and the propeller 2 may be a two-blade pulp, a three-bladed paddle or a four-bladed paddle, etc.;
- the main role of 121 is to increase the lift of the aircraft.
- the high-speed motor 82 can make the rotation speed of the propeller 2 faster, thereby further increasing the lift of the aircraft; in particular, the high-speed motor 82 referred to in this embodiment can reach a maximum speed of 33,000 ⁇ 1000 rpm during sudden stop or take-off. /min, and, by increasing the voltage of 1 volt, the rotational speed per minute can be increased by 3,400 rpm; it should be noted that in order to reduce the energy consumption, the rotational speed of the motor 82 can be appropriately reduced during the flight of the aircraft.
- the rechargeable battery 81 is used to provide energy to the aircraft; if the lift is sufficient, the capacity of the battery 81 can be appropriately increased to extend the life of the aircraft. It should be noted that one motor 82 is used to drive one propeller 2.
- the load of the entire aircraft can be allowed to reach about 180 grams; A typical 60 mm two-leaf pulp has a load of only 50-60 grams.
- the inlet leading edge will form a larger negative pressure zone, thereby creating an additional upward pulling force; at the same time, the wall surface of the ducting 121 can also improve the air flow characteristics of the blade tip region to reduce the induction at the tip of the blade. Resistance, increase the lift of the blade rotation; the above-mentioned reverse thrust and tension and the reduced induced resistance force can significantly increase the lift of the aircraft. Therefore, the provision of the duct 121 can reduce the size of the propeller 2 blade. The aircraft still maintains a high load, a large battery life and a large lift.
- a blade guard 3 disposed on the duct casing 12 is further included.
- the number of the engaging slots 32 is equal to the number of the engaging blocks 122, and each of the engaging blocks 122 corresponds to one engaging slot 32; the clamping duct 12 and the blade guard cover are arranged by means of a clamping manner.
- the disassembly between the three is more convenient to operate; and the engaging groove 32 can also function as a limit, that is, after the engaging groove 32 and the engaging block 122 are connected, the blade protection cover 3 can be avoided during use of the aircraft.
- the duct shell 12 is rotated in the circumferential direction.
- the blade guard cover 3 is provided with a fixing block 31, and the engaging groove 32 is disposed on the fixing block 31; one side of the engaging block 122 is located at the convex portion A notch 123 is provided on the rim 124; the fixing block 31 can pass through the notch 123.
- the shock absorbing mechanism 4 is further included, and the shock absorbing mechanism 4 is used to buffer the impact force caused by the rotation of the propeller 2;
- the vibration bracket 41 and the elastic member are connected to the main frame 1 through elastic members, and the PCB board 6 of the aircraft is disposed on the shock absorbing bracket 41.
- the PCB board 6 is disposed on the damper bracket 41.
- the damper bracket 41 is connected to the main frame 1 through an elastic member.
- the elastic member buffers the vibration force by its own expansion and contraction action. Therefore, the impact force of the shock absorbing bracket 41 is reduced, and the PCB board 6 is further protected, and the gyroscope can be operated under relatively stable conditions, thereby increasing the accuracy of the test.
- the elastic member is a rubber ball 42.
- an analog lens 5 is further included, and the analog lens 5 is disposed on the damper bracket 41.
- the landing gear is further included, and the landing gear is disposed on the frame 1.
- the aircraft of the present embodiment provides a vertical take-off and landing mode. Therefore, in order to reduce the impact force of the ground on the aircraft when landing, a landing gear is disposed on the frame 1; specifically, as shown in FIG.
- the landing gear is disposed on the main frame 1, the landing gear includes a plurality of landing support bars 7, and each of the propellers 2 is provided with a landing support bar 7 below.
- the motor 82 and the propeller 2 are both disposed on the fixed casing 13, and the plurality of support rods 14 are simultaneously connected to the duct casing 12 and the fixed casing 13, so that the stability of the overall structure can be increased.
- the protective rod 15 is disposed on the plurality of support rods 14, which reduces the chance of the operator contacting the propeller 2 and provides a certain protection to the operator.
- a button is provided on the body cover 9, which is connected to the drive mechanism 8 for opening and closing the aircraft; and the button can also be connected to the lamp cover of the aircraft to open and close the lamp cover.
- the aircraft of the present embodiment includes an upper cover 1, a propeller 2, a duct 31, a straight portion 311, an outer expansion portion 312, a motor mount 32, a support frame 33, a connecting post 34, and a base. 35.
- the aircraft of the present invention includes a propeller 2, and the aircraft further includes ducts 31 respectively disposed outside the propellers 2, wherein the ducts 31 include a straight portion 311 and an outer portion located above the straight portion 311. 312, the opening of the flared portion 312 is larger than the opening of the straight portion 311.
- the aircraft of this embodiment further includes a base 35 to which the ducts 31 are attached.
- an upper cover 1 is provided over the base 35. Both ends of the base 35 are provided with a connecting post 34 for fixing the upper cover, and the connecting post 34 is disposed through the upper cover 1. Thereby, both ends of the upper cover 1 are locked by the connecting post 34, thereby fixing the upper cover 1.
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Toys (AREA)
Abstract
Description
Claims (21)
- 一种飞行器,其特征在于,包括:机架、螺旋桨、涵道和驱动机构,所述涵道设置在所述机架上,用于增加所述飞行器的升力;所述螺旋桨设置在所述涵道内,且与所述机架连接;所述驱动机构与所述螺旋桨连接,且设置在所述机架上。
- 如权利要求1所述的飞行器,其特征在于,所述机架包括主机架,所述涵道包括圆柱形的涵道壳,所述涵道壳设置在所述主机架的侧面上;所述涵道壳围设而成一内部空间。
- 如权利要求2所述的飞行器,其特征在于,还包括设置在所述涵道壳上的桨叶保护罩。
- 如权利要求3所述的飞行器,其特征在于,所述涵道壳的边沿设置有向外延伸的凸缘,所述凸缘上设置有多个卡合块;所述桨叶保护罩上设置有卡合槽,所述卡合槽与所述卡合块配合将所述桨叶保护罩固定在所述涵道壳上。
- 如权利要求4所述的飞行器,其特征在于,所述桨叶保护罩上设置有固定块,所述卡合槽设置在所述固定块上;所述卡合块的一侧且位于所述凸缘上设置有缺口;所述固定块能够通过所述缺口。
- 如权利要求2所述的飞行器,其特征在于,还包括减震机构,所述减震机构用于缓冲所述螺旋桨旋转所带来的冲击力;所述减震机构包括减震机架和弹性件,所述减震机架通过所述弹性件与所述主机架连接,所述飞行器的PCB板设置在所述减震机架上。
- 如权利要求6所述的飞行器,其特征在于,所述弹性件为橡胶球。
- 如权利要求6所述的飞行器,其特征在于,还包括模拟镜头,所述模拟镜头设置在所述减震机架上。
- 如权利要求1-8至少一项一项所述的飞行器,其特征在于,还包括起落架,所述起落架设置在所述机架上。
- 如权利要求1-8至少一项所述的飞行器,其特征在于,所述驱动机构包括高转速的马达和可充电的电池,所述电池与所述马达电连接,所述马达的输出轴与所述螺旋桨连接;所述电池和所述马达均设置在所述机架上。
- 如权利要求1所述的飞行器,其特征在于,所述涵道包括直筒部和位于所述直筒部上方的外扩部,所述外扩部的开口大于所述直筒部的开口。
- 如权利要求11所述的飞行器,其特征在于,所述外扩部的形状为喇叭状。
- 如权利要求11或12所述的飞行器,其特征在于,所述涵道内设置有马达固定座,所述马达固定座通过支撑架与所述涵道的内壁连接,所述马达固定座内设置有马达,所述马达与所述螺旋桨连接。
- 如权利要求13所述的飞行器,其特征在于,所述马达固定座伸出于所述涵道,且所述马达固定座用于起落支撑。
- 如权利要求11-14至少一项所述的飞行器,其特征在于,所述涵道的数量为4个。
- 如权利要求13所述的飞行器,其特征在于,所述飞行器还包括一基座,所述涵道连接在所述基座上。
- 如权利要求16所述的飞行器,其特征在于,所述涵道、所述支撑架、所述马达固定座、所述基座为一体成型。
- 如权利要求16所述的飞行器,其特征在于,所述基座上方盖设有一上盖。
- 如权利要求18所述的飞行器,其特征在于,所述基座的两端设置有用于固定所述上盖的连接柱,所述连接柱穿设于所述上盖。
- 如权利要求18所述的飞行器,其特征在于,所述基座上设置有垫座,一主控板固定于所述垫座。
- 如权利要求18所述的飞行器,其特征在于,所述垫座上设置有减震垫圈,所述减震垫圈用于支撑所述上盖。
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US15/578,452 US10604243B2 (en) | 2015-07-17 | 2016-07-15 | Aerial vehicle |
CA2988351A CA2988351C (en) | 2015-07-17 | 2016-07-15 | Aerial vehicle |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201520523471.0 | 2015-07-17 | ||
CN201520523471.0U CN204956910U (zh) | 2015-07-17 | 2015-07-17 | 旋翼飞行器 |
CN201521081802.6 | 2015-12-22 | ||
CN201521081802.6U CN205440860U (zh) | 2015-12-22 | 2015-12-22 | 飞行器 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2017012515A1 true WO2017012515A1 (zh) | 2017-01-26 |
Family
ID=57833760
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/CN2016/090193 WO2017012515A1 (zh) | 2015-07-17 | 2016-07-15 | 飞行器 |
Country Status (3)
Country | Link |
---|---|
US (1) | US10604243B2 (zh) |
CA (1) | CA2988351C (zh) |
WO (1) | WO2017012515A1 (zh) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN107472523A (zh) * | 2017-09-20 | 2017-12-15 | 湖南基石信息技术有限公司 | 涵道推进器及小型无人飞机 |
Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10780979B2 (en) * | 2016-11-14 | 2020-09-22 | Intel IP Corporation | Drone rotor cage |
US10675932B2 (en) * | 2017-03-08 | 2020-06-09 | Toyota Motor Engineering & Manufacturing North America, Inc. | Dual-mode vehicle with wheel rotors |
CN108033003A (zh) * | 2018-01-11 | 2018-05-15 | 深圳市中联讯科技有限公司 | 一种飞行器防护罩以及飞行器 |
USD906170S1 (en) * | 2018-02-13 | 2020-12-29 | Skydio, Inc. | Unmanned aerial vehicle |
CN108974337A (zh) * | 2018-07-23 | 2018-12-11 | 深圳市中联讯科技有限公司 | 一种飞行器保护罩 |
CN111572760B (zh) * | 2020-05-07 | 2022-11-11 | 重庆交通大学 | 一种无人机用起落架减震控制系统及方法 |
USD938860S1 (en) * | 2020-05-22 | 2021-12-21 | Liying Bao | Unmanned aerial vehicle |
JP1672470S (zh) * | 2020-06-26 | 2020-11-16 | ||
USD985425S1 (en) * | 2020-07-24 | 2023-05-09 | Sang Hyun Lee | Drone |
CN112706915A (zh) * | 2021-01-05 | 2021-04-27 | 陆颖怡 | 一种气压高度检测装置无人机 |
US20220380043A1 (en) * | 2021-05-25 | 2022-12-01 | Hydronalix, Inc. | Unmanned aerial vehicle with underwater sonar scanning capability |
USD1017463S1 (en) * | 2021-11-17 | 2024-03-12 | MerchSource, LLC | Toy drone |
USD1008873S1 (en) * | 2021-11-24 | 2023-12-26 | Ruichun Lin | Aerial vehicle |
USD988927S1 (en) * | 2022-09-29 | 2023-06-13 | Mingfeng Huang | Remote-controlled drone |
Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH0370699A (ja) * | 1989-08-09 | 1991-03-26 | Hitachi Zosen Corp | 垂直離着飛行体の飛行制御方法 |
WO2006112578A1 (en) * | 2005-04-20 | 2006-10-26 | Won-Sup Oh | Vertical take-off and landing aircraft |
CN201632051U (zh) * | 2009-10-30 | 2010-11-17 | 深圳市艾特航模股份有限公司 | 一种带安全框的双桨直升机 |
DE102011117605A1 (de) * | 2011-11-04 | 2013-05-08 | UNITED pds GmbH | Fluggerät nach dem Prinzip eines Hubschraubers |
CN203090471U (zh) * | 2013-01-11 | 2013-07-31 | 河南科技大学 | 一种四旋翼飞行器的机体 |
CN203264279U (zh) * | 2013-06-03 | 2013-11-06 | 邱志宏 | 一种多轴飞行器 |
CN203889065U (zh) * | 2014-06-20 | 2014-10-22 | 杜卫国 | 一种带有环翼涵道的飞行器 |
CN204170422U (zh) * | 2014-10-25 | 2015-02-25 | 杜超 | 一种涵道风扇式的多轴飞行器 |
CN204956910U (zh) * | 2015-07-17 | 2016-01-13 | 优利科技有限公司 | 旋翼飞行器 |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE19940678A1 (de) * | 1998-08-28 | 2000-05-25 | Toyoda Automatic Loom Works | Montagestruktur für einen Sensor in einem Industriefahrzeug und Industriefahrzeug |
US8328130B2 (en) * | 2008-12-08 | 2012-12-11 | Honeywell International Inc. | Vertical take off and landing unmanned aerial vehicle airframe structure |
US7971827B2 (en) * | 2009-04-27 | 2011-07-05 | Barrientos Ernesto D | Bird collision prevention device for an aircraft |
KR101042200B1 (ko) * | 2010-09-02 | 2011-06-16 | 드림스페이스월드주식회사 | Pcb를 사용한 무인 비행체 |
CN102980584B (zh) * | 2011-09-02 | 2017-12-19 | 深圳市大疆创新科技有限公司 | 一种无人飞行器惯性测量模块 |
US20130233964A1 (en) * | 2012-03-07 | 2013-09-12 | Aurora Flight Sciences Corporation | Tethered aerial system for data gathering |
EP2911937B1 (en) * | 2012-10-26 | 2017-03-29 | LORD Corporation | Hub-mounted active vibration control (havc) devices, systems, and methods |
US20140145026A1 (en) | 2012-11-28 | 2014-05-29 | Hans Skjersaa | Unmanned Aerial Device |
CA2936329A1 (en) * | 2014-01-07 | 2015-07-16 | 4525612 Canada Inc. Dba Maginaire | Personal flight vehicle |
US9889930B2 (en) * | 2014-11-24 | 2018-02-13 | Amazon Technologies, Inc. | Unmanned aerial vehicle protective frame configuration |
US10059437B2 (en) * | 2015-01-08 | 2018-08-28 | Robert Stanley Cooper | Multi-rotor safety shield |
WO2016112124A2 (en) * | 2015-01-08 | 2016-07-14 | Vantage Robotics, Llc | Unmanned aerial vehicle with propeller protection and high impact survivability |
CN113959440A (zh) * | 2015-04-07 | 2022-01-21 | 深圳市大疆创新科技有限公司 | 用于提供简单而可靠的惯性测量单元的系统和方法 |
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2016
- 2016-07-15 CA CA2988351A patent/CA2988351C/en active Active
- 2016-07-15 US US15/578,452 patent/US10604243B2/en active Active
- 2016-07-15 WO PCT/CN2016/090193 patent/WO2017012515A1/zh active Application Filing
Patent Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH0370699A (ja) * | 1989-08-09 | 1991-03-26 | Hitachi Zosen Corp | 垂直離着飛行体の飛行制御方法 |
WO2006112578A1 (en) * | 2005-04-20 | 2006-10-26 | Won-Sup Oh | Vertical take-off and landing aircraft |
CN201632051U (zh) * | 2009-10-30 | 2010-11-17 | 深圳市艾特航模股份有限公司 | 一种带安全框的双桨直升机 |
DE102011117605A1 (de) * | 2011-11-04 | 2013-05-08 | UNITED pds GmbH | Fluggerät nach dem Prinzip eines Hubschraubers |
CN203090471U (zh) * | 2013-01-11 | 2013-07-31 | 河南科技大学 | 一种四旋翼飞行器的机体 |
CN203264279U (zh) * | 2013-06-03 | 2013-11-06 | 邱志宏 | 一种多轴飞行器 |
CN203889065U (zh) * | 2014-06-20 | 2014-10-22 | 杜卫国 | 一种带有环翼涵道的飞行器 |
CN204170422U (zh) * | 2014-10-25 | 2015-02-25 | 杜超 | 一种涵道风扇式的多轴飞行器 |
CN204956910U (zh) * | 2015-07-17 | 2016-01-13 | 优利科技有限公司 | 旋翼飞行器 |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN107472523A (zh) * | 2017-09-20 | 2017-12-15 | 湖南基石信息技术有限公司 | 涵道推进器及小型无人飞机 |
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US10604243B2 (en) | 2020-03-31 |
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