WO2018196123A1 - Hélice, système de propulsion et aéronef sans pilote - Google Patents

Hélice, système de propulsion et aéronef sans pilote Download PDF

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Publication number
WO2018196123A1
WO2018196123A1 PCT/CN2017/088334 CN2017088334W WO2018196123A1 WO 2018196123 A1 WO2018196123 A1 WO 2018196123A1 CN 2017088334 W CN2017088334 W CN 2017088334W WO 2018196123 A1 WO2018196123 A1 WO 2018196123A1
Authority
WO
WIPO (PCT)
Prior art keywords
propeller
foolproof
rib
driving device
blade seat
Prior art date
Application number
PCT/CN2017/088334
Other languages
English (en)
Chinese (zh)
Inventor
陈鹏
邓涛
江彬
Original Assignee
深圳市大疆创新科技有限公司
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 深圳市大疆创新科技有限公司 filed Critical 深圳市大疆创新科技有限公司
Priority to CN201780065071.1A priority Critical patent/CN109890699A/zh
Publication of WO2018196123A1 publication Critical patent/WO2018196123A1/fr

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Classifications

    • 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
    • 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
    • B64C11/02—Hub construction
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors

Definitions

  • the invention relates to the field of aircraft, and in particular to a propeller, a power system and an unmanned aerial vehicle.
  • Propellers are often used as power propellers for aircraft or ships.
  • the propeller generally includes a paddle, a paddle mount on which the paddle is mounted, and a drive unit coupled to the paddle mount.
  • the driving device drives the paddle seat to rotate while driving the blades to rotate together.
  • the fixed connection manner of the blade seat and the driving device includes a manner of fixed connection or snap connection by screwing.
  • a typical multi-rotor UAV usually requires multiple propellers.
  • it usually includes four propellers, in which two propellers on the diagonal rotate in the same direction, and the adjacent two propellers rotate in opposite directions.
  • the adjacent two propellers it is necessary for the adjacent two propellers to have a distinction between the positive and negative propellers, thereby providing lift for the aircraft.
  • the shape of several propellers is generally the same. Therefore, when the user performs assembly, there will be a slight negligence, and there will be problems with the anti-propellers, which will affect the flight of the UAV, and more serious. It will cause the UAV to fall and be damaged.
  • the present invention provides a structure that is robust and can be driven in a predetermined direction with the drive.
  • a propeller for connecting to a driving device and capable of rotating under the driving of the driving device, the propeller comprising a blade seat and a blade connected to the blade seat, the blade seat comprising a plurality of buckles a plurality of the fastening portions for fasteningly connecting with the driving device, the blade holder further comprising at least one first foolproof portion corresponding to the fastening portion, the first foolproof portion The portion is abutted against the corresponding fastening portion for defining the blade seat to be coupled to the driving device in a predetermined direction.
  • first foolproof portion and the fastening portion are integrally formed.
  • the fastening portion includes a rib and a rib extending from the blade seat, and the rib is formed at an end of the rib.
  • the rib and the baffle are perpendicular to each other.
  • the rib is vertically connected to the blade seat, and the rib is disposed at an end of the rib and protrudes radially outward toward a rotation direction of the propeller.
  • the height of the rib is greater than the height of the first fool.
  • a center of the paddle seat is provided with a connecting hole for connecting the propeller and the driving device, and the first foolproof portion and a side of the rib facing the connecting hole are abutted Pick up.
  • the number of the first foolproof portions is the same as the number of the fastening portions, and the plurality of the fastening portions are in contact with the plurality of the foolproof portions in one-to-one correspondence.
  • the fastening portion is evenly disposed around the connecting hole.
  • the propeller is a folding paddle.
  • a power system including a driving device and a propeller as described above, the propeller passing The fastening portion is connected to the driving device.
  • the driving device is provided with a second foolproof portion that cooperates with the first foolproof portion, and when the propeller is not connected to the driving device in the predetermined direction, the first foolproofing The portion is docked with the second foolproof portion to prevent the propeller from being mounted on the driving device.
  • An unmanned aerial vehicle comprising a power system as described above.
  • the propeller in the power system of the embodiment of the present invention is buckled with the driving device in a snap manner.
  • the fastening portion of the propeller is disposed in contact with the first foolproof portion, so that the blade seat can be defined to be connected to the driving device in a predetermined direction; and the fastening portion and the first defense
  • the structure in which the stay is abutted is easy to shape and has a firm structure.
  • FIG. 1 is a schematic perspective view of a power system according to an embodiment of the present invention.
  • FIG. 2 is a schematic exploded view of the power system of FIG. 2.
  • FIG. 3 is a schematic exploded view of another angle of the power system of FIG. 3.
  • FIG. 4 is a perspective assembled view of the driving device of FIG. 1.
  • the present invention provides a power system 100 that includes a drive unit 10 and a propeller 20.
  • the driving device 10 is buckled with the propeller 20 by a snapping manner for driving the propeller 20 to rotate.
  • the driving device 10 includes a main body portion 12, an elastic abutting member 13 disposed on the main body portion 12, a locking portion 14 disposed on the main body portion 12, and a main body portion 12 and A drive shaft 15 that rotates relative to the main body portion 12.
  • the body portion 12 includes a bearing surface 120.
  • the bearing surface 120 is disposed adjacent to the propeller 20.
  • the main body portion 12 is cylindrical, and the drive shaft 15 protrudes from a central position of the main body portion 12.
  • a positioning hole 1200 is defined in the bearing surface 120.
  • the positioning hole 1200 is a plurality of discrete circular holes, and the circular holes are arranged in an annular array around the driving shaft.
  • the positioning hole 1200 is not limited to a circular shape, and may also be a square hole or a positioning groove.
  • the number and arrangement of the positioning holes 1200 may also be other manners. limited.
  • the positioning hole 1200 is spaced apart from the middle by a plurality of first mounting holes 1201, the positioning holes 1200 and a plurality of the first mounting holes 1201 is used to connect the locking portion 14.
  • the elastic resisting member 13 is sleeved on the driving shaft 15 .
  • the elastic resisting member 13 is an elastic member.
  • the elastic member is a spring.
  • the spring is directly sleeved on the drive shaft 15 . When the spring is compressed in one direction, it provides an elastic restoring force in the opposite direction.
  • the locking portion 14 is disposed on the top of the main body portion 12 . In other embodiments, the locking portion 14 can also be integrally formed with the main body portion 12.
  • the latching portion 14 is provided with at least one latching portion 140 for engaging with the propeller 20.
  • the latching portion 140 is a plurality of through holes, and the stepped block 146 is disposed in the through hole. Further, the step block 146 is disposed on one side of the through hole, and the height of the step block 146 is smaller than the depth of the through hole, so that the step block 146 blocks a part of the perforation without being blocked by the step block 146.
  • the perforated portion forms a set of inlets 26 that extend through the locking portion 14.
  • the locking portion 14 is substantially disc-shaped.
  • the shape of the locking portion 14 can be designed as needed, for example, elliptical, rectangular, square, or the like.
  • the locking portion 14 is provided with a through hole 1410 corresponding to the drive shaft 15 for the drive shaft 15 to pass through.
  • Each of the perforations extends in a circular arc shape with an axis of the through hole 1410 and is equidistant from the through hole 1410.
  • the locking portion 14 is provided with a plurality of second mounting holes 1411 corresponding to the plurality of the first mounting holes 1201 .
  • a plurality of the second mounting holes 1411 are in one-to-one correspondence with the plurality of first mounting holes 1201.
  • a positioning portion 144 is disposed on the locking portion 14 , and the positioning portion 144 is disposed on a surface of the locking portion 14 facing the main body portion 12 .
  • the positioning unit 144 A plurality of cylinders are formed protruding from the bottom of the locking portion 14, and the number and position of the cylinders coincide with the positioning holes 1200 on the main body portion 12.
  • the locking portion 14 is recessed toward a side of the main body portion 12 to form a receiving groove 145.
  • the receiving groove 145 is coaxial with the through hole 1401.
  • One end of the elastic resisting member 13 is received in the receiving groove 145 and is limited to the main body portion 12 .
  • the elastic resisting member 13 is sleeved on the driving shaft 15, and the locking portion 14 is placed on the bearing surface 120.
  • the driving shaft 15 is inserted through the lock.
  • the positioning portion 144 of the locking portion 14 faces the bearing surface 120 of the main body portion 12 , and the positioning portion 144 is received in the main body portion 12 .
  • a plurality of the second mounting holes 1411 are respectively aligned with the first mounting hole 1201, and finally the locking portion 14 is fixed to the main body portion 12 by a fastener.
  • the propeller 20 includes a paddle holder 21 and two or more blades 22 coupled to the paddle holder 21.
  • the paddle seat 21 is detachably disposed on the locking portion 14.
  • One side of the paddle seat facing the drive bearing surface 120 is a connecting surface 211.
  • the connecting surface 211 of the paddle seat 21 is disposed opposite to the bearing surface 120.
  • a connecting hole 2311 is defined in the connecting surface 211 for receiving the driving shaft 15 .
  • the fastening portion 230 includes a rib 231 and a rib 232.
  • the rib 231 is formed to extend perpendicularly from the connecting surface 211 of the blade holder 21, and the rib 232 is formed on the The end of the rib 231 protrudes in a direction away from the connecting hole 2311.
  • the crosspiece 232 and the rib 231 are perpendicular to each other.
  • the fastening portion 230 is evenly disposed around the connecting hole 2311.
  • the number of the ribs 231 is three, and the three ribs 231 are arranged in an annular array around the connecting holes 2311. It is understood that, in other embodiments, the The number of ribs 231 may also be one, two, four, and the like.
  • a first foolproof portion 251 is further formed between each of the ribs 231 and the connecting hole 2311. Specifically, the first foolproof portion 251 is disposed on the connecting surface 211 of the blade holder 21 and is disposed to abut one side of the connecting hole 2311.
  • the number of the first foolproof portions 251 may be the same as the number of the ribs 231, and the first foolproof portion 251 is disposed in one-to-one correspondence with the ribs 231; the first foolproof portion 251
  • the number of the first foolproof portions 251 abutting one of the ribs 231 facing the connecting hole 2311 is set to be one when the number of the first foolproof portions 251 is one.
  • the purpose of the foolproof can also be achieved, which is not limited by the present invention.
  • the first foolproof portion 251 has a substantially rectangular parallelepiped shape, the number of the first foolproof portions 251 is three, and the three first foolproof portions 251 and the three ribs 231 one-to-one correspondence. In other words, the three first foolproof portions 251 are respectively abutted on one surface of the corresponding rib 231 facing the connecting hole 2311. In the present embodiment, the rib 231 and the first foolproof portion 251 corresponding to the rib 231 are integrally formed.
  • the design of the first foolproof portion 251 abutting against the rib 231 is not only easy to shape, but the abutment of the first foolproof portion 251 against the rib 231 can enhance the joint strength of the rib 231;
  • the first foolproof portion 251 can be used to define the blade seat 21 along the predetermined direction with the driving device 10
  • the first foolproof portion 251 is connected to the blade holder 11 and is identical to the extending direction of the rib 231.
  • the locking portion 14 is further formed with a second foolproof portion 252, and the second foolproof portion 252 extends opposite to the first foolproof portion 251, and the heights of the two are equal and mutually matched to prevent Staying effect.
  • the first foolproof portion 251 and the second foolproof portion 252 function as a foolproof.
  • the first foolproof portion 251 and the second foolproof portion 252 can be offset from each other such that the propeller 20 is engaged with the lock
  • the portion 14 can be mounted; when the propeller 20 is coupled to the locking portion 14 in the wrong direction or angle, the first foolproof portion 251 and the second foolproof portion 252 can be docked with each other, thereby increasing
  • the installation distance between the propeller 20 and the locking portion 14 is such that the two cannot be connected, that is, the propeller 20 is prevented from being mounted on the driving device 10.
  • the first foolproof portion 251 and the second foolproof portion 252 cooperate to restrict the blade seat from being coupled to the drive device in a direction other than the predetermined direction.
  • the fastening portion 230 may be disposed on the bearing surface 120 of the main body portion 12, and the corresponding first anti-slipping portion 251 is also disposed on the bearing surface 120 at the same time.
  • the fastening portion 230 is abutted. Thereby, the propeller 20 and the driving device 10 can be fastened in a predetermined direction.
  • the locking portion 14 is connected to the connecting surface 211 of the blade holder 21, thereby achieving the locking and fixing of the propeller 20 and the driving device 10. It can be understood that the locking portion 14 and the blade holder 21 are integrally formed at this time.
  • the drive shaft 15 When assembling, the drive shaft 15 is first assembled into the connecting hole 2311 by an interference fit, and the concentricity and the vertical between the propeller 20 and the driving device 10 are predetermined. Straightness, the rib 232 of the paddle seat 21 extends into the set of inlets 26 through the latching portion 140 of the locking portion 14, and then, the blade seat 21 of the propeller 20 is depressed, The elastic resisting member 13 is deformed by the connecting hole 2311, and the propeller 20 is rotated in a predetermined direction, that is, in the grouping direction, so that the bar 232 is assembled under the step block 146 of the locking portion 14.
  • the elastic resisting member 13 elastically resists the blade seat 21, and the elastic resisting member 13 acts as an elastic force, and each of the brace 232 is correspondingly held by the retaining member.
  • the propeller 20 is in a locked state.
  • the blade holder 21 When the propeller 20 needs to be detached from the driving device 10, the blade holder 21 is depressed, and the elastic abutting member 13 is pressed down by the blade holder 21 to make the dam 232 leaves the step block 146 and rotates the propeller 20 in a direction opposite to the grouping direction. At this time, the propeller 20 is in an unlocked state, and the bar 232 is detached from the step block 146 side. A baffle 232 is retracted into the set of inlets 26 to effect separation of the propeller 20 from the drive unit 10.
  • the present invention also provides an unmanned aerial vehicle including the power system 100.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Toys (AREA)
  • Connection Of Plates (AREA)

Abstract

L'invention concerne une hélice (20), un système de propulsion (100) comprenant l'hélice (20), et un aéronef sans pilote comprenant le système de propulsion (100). L'hélice (20) est conçue pour être reliée à un dispositif d'entraînement (10) et peut être entraînée par le dispositif d'entraînement (10) de façon à tourner; l'hélice (20) comprend une base (21) et des pales (22) reliées à la base (21); la base de pales (21) comprend une pluralité de parties d'encliquetage (230) qui peuvent être reliées de manière sûre au dispositif d'entraînement (10) dans une direction prédéterminée; la base de pales (21) comprend en outre une première partie indéréglable (251) prévue correspondant à au moins une partie d'encliquetage (230); la première partie indéréglable (251) vient en butée contre la partie d'encliquetage correspondante (230) et peut empêcher le raccordement de la base de pales (21) au dispositif d'entraînement (10) le long d'une direction autre que la direction prédéterminée. La partie d'encliquetage (230) et la première partie indéréglable (251) de l'hélice (20) viennent en butée l'une contre l'autre, de sorte que l'hélice (20) ne peut être raccordée qu'au dispositif d'entraînement (10) dans la direction prédéterminée; en outre, la structure de la partie d'encliquetage (230) et de la première partie indéréglable (251), venant en butée l'une contre l'autre, est facile à définir et à gérer.
PCT/CN2017/088334 2017-04-25 2017-06-14 Hélice, système de propulsion et aéronef sans pilote WO2018196123A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201780065071.1A CN109890699A (zh) 2017-04-25 2017-06-14 螺旋桨、动力系统及无人飞行器

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201720454103.4 2017-04-25
CN201720454103.4U CN206766327U (zh) 2017-04-25 2017-04-25 螺旋桨、动力系统及无人飞行器

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WO2018196123A1 true WO2018196123A1 (fr) 2018-11-01

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Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108127066B (zh) * 2017-12-22 2019-06-25 深圳市道通智能航空技术有限公司 螺旋桨装配方法、组装夹具及螺旋桨
CN109969389A (zh) * 2017-12-28 2019-07-05 昆山优尼电能运动科技有限公司 一种桨叶连接结构
CN109969385A (zh) * 2017-12-28 2019-07-05 辽宁壮龙无人机科技有限公司 无人机及其螺旋桨
WO2020103055A1 (fr) * 2018-11-21 2020-05-28 深圳市大疆创新科技有限公司 Ensemble rotor et véhicule aérien sans pilote
CN109677595A (zh) * 2019-01-29 2019-04-26 深圳市律远汇智科技有限公司 一种用于航拍的便于收纳的无人飞行装置
WO2021134590A1 (fr) * 2019-12-31 2021-07-08 深圳市大疆创新科技有限公司 Hélice, système de propulsion et aéronef sans pilote
CN116710358A (zh) * 2021-05-14 2023-09-05 深圳市大疆创新科技有限公司 螺旋桨、动力装置、动力系统及无人飞行器

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US4611972A (en) * 1984-05-31 1986-09-16 Ralph Andrae Aeroplane propeller
CN104986330A (zh) * 2015-06-29 2015-10-21 深圳一电科技有限公司 桨臂连接组件及飞行器
CN106516103A (zh) * 2016-11-24 2017-03-22 腾讯科技（深圳）有限公司 一种多旋翼无人机
WO2017049607A1 (fr) * 2015-09-25 2017-03-30 深圳市大疆创新科技有限公司 Ensemble rotor et véhicule aérien sans pilote comprenant celui-ci
CN206107533U (zh) * 2016-08-31 2017-04-19 深圳市大疆创新科技有限公司 驱动装置、螺旋桨及动力系统

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GB2482545B (en) * 2010-08-06 2017-05-03 Ge Aviat Systems Ltd Aircraft propellers with composite blades mounted to a single propeller hub
WO2016074133A1 (fr) * 2014-11-10 2016-05-19 深圳市大疆创新科技有限公司 Dispositif d'entrainement, hélice et système d'alimentation
CN105730690A (zh) * 2016-04-06 2016-07-06 浙江大华技术股份有限公司 一种螺旋桨装置及无人飞行器
CN205499352U (zh) * 2016-04-06 2016-08-24 浙江大华技术股份有限公司 一种螺旋桨装置及无人飞行器
CN205770147U (zh) * 2016-07-18 2016-12-07 成都纵横大鹏无人机科技有限公司 螺旋桨锁定装置、垂直起降组件及无人机

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Publication number Priority date Publication date Assignee Title
US4611972A (en) * 1984-05-31 1986-09-16 Ralph Andrae Aeroplane propeller
CN104986330A (zh) * 2015-06-29 2015-10-21 深圳一电科技有限公司 桨臂连接组件及飞行器
WO2017049607A1 (fr) * 2015-09-25 2017-03-30 深圳市大疆创新科技有限公司 Ensemble rotor et véhicule aérien sans pilote comprenant celui-ci
CN206107533U (zh) * 2016-08-31 2017-04-19 深圳市大疆创新科技有限公司 驱动装置、螺旋桨及动力系统
CN106516103A (zh) * 2016-11-24 2017-03-22 腾讯科技（深圳）有限公司 一种多旋翼无人机

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