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WO2019082044A1 - Mécanisme à une seule main de montage et de démontage rapide d'une hélice - Google Patents

Mécanisme à une seule main de montage et de démontage rapide d'une hélice

Info

Publication number
WO2019082044A1
WO2019082044A1 PCT/IB2018/058184 IB2018058184W WO2019082044A1 WO 2019082044 A1 WO2019082044 A1 WO 2019082044A1 IB 2018058184 W IB2018058184 W IB 2018058184W WO 2019082044 A1 WO2019082044 A1 WO 2019082044A1
Authority
WO
WIPO (PCT)
Prior art keywords
propeller
locking
locking lever
lever arms
levers
Prior art date
Legal status (The legal status 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 status listed.)
Ceased
Application number
PCT/IB2018/058184
Other languages
English (en)
Inventor
Mehta ANKIT
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Ideaforge Technology Pvt Ltd
Original Assignee
Ideaforge Technology Pvt Ltd
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 Ideaforge Technology Pvt Ltd filed Critical Ideaforge Technology Pvt Ltd
Publication of WO2019082044A1 publication Critical patent/WO2019082044A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

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
    • B64C11/02—Hub construction
    • 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
    • B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
    • B64U30/291—Detachable rotors or rotor supports
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/13—Propulsion using external fans or propellers

Definitions

  • the present disclosure generally relates to the field of Aerial vehicles (AV).
  • AV Aerial vehicles
  • the present disclosure pertains to a quick mounting and dismounting mechanism for a propeller on the AV.
  • Aerial Vehicles including Unmanned Aerial Vehicles are well known in the art.
  • a propeller system of UAVs generally comprises a propeller, a propeller seat body on which the propeller is mounted, and a drive shaft connected to the propeller seat body.
  • the drive shaft rotates under action of a motor to drive the propeller.
  • assembly of the propeller and the propeller seat body, i.e. rotor is fastened to the drive shaft using fasteners such as screws, nuts, and pins.
  • fasteners such as screws, nuts, and pins.
  • the conventional fastening method also requires more time for mounting and dismounting of the propellers and is complex.
  • WIPO Patent Application number WO2017028503 discloses a propeller connection structure comprising a motor rotor housing, a propeller holder and a propeller mount.
  • Two movable buckle mechanisms are provided - one on either side of the propeller holder, with an elastic member placed between them for detachably connecting the propeller to the propeller mount.
  • the elastic members enable the movable buckle to displace outward when the propeller with the propeller mount is pressed onto the propeller holder for locking.
  • the propeller is removed from the propeller mount by pressing the two movable buckles inwardly.
  • This quick disassembly structure holds the propeller only by the elasticity of the metal buckles and carries risk of propeller detachment when the rotation of the motor changes.
  • such quick disassembly structures requires a dedicated propeller to form the snap-fit shall not be compatible with any other kind of propellers mounting installation.
  • the utility of the present invention is to overcome the above-mentioned deficiencies of the prior art, and in providing a propeller quick mounting and dismounting mechanism that can be operated with single hand.
  • the mechanism further incorporates an improved locking feature.
  • the numbers expressing quantities of ingredients, properties such as concentration, reaction conditions, and so forth, used to describe and claim certain embodiments of the invention are to be understood as being modified in some instances by the term "about.” Accordingly, in some embodiments, the numerical parameters set forth in the written description and attached claims are approximations that can vary depending upon the desired properties sought to be obtained by a particular embodiment. In some embodiments, the numerical parameters should be construed in light of the number of reported significant digits and by applying ordinary rounding techniques. Notwithstanding that the numerical ranges and parameters setting forth the broad scope of some embodiments of the invention are approximations, the numerical values set forth in the specific examples are reported as precisely as practicable. The numerical values presented in some embodiments of the invention may contain certain errors necessarily resulting from the standard deviation found in their respective testing measurements.
  • a general object of the present disclosure is to simplify attaching/detaching a propeller of an Aerial Vehicle such as an UAV, with motor.
  • An object of the present disclosure is to provide a simple, quick mounting and dismounting, cost effective and secure mechanism for propeller mounting in an Aerial Vehicles that can be operated with a single hand.
  • An object of the present disclosure is to provide a single-handedly locking/detaching mechanism for quick mounting and dismounting of a propeller forAerial Vehicles.
  • Another object of the present disclosure is to provide a quick propeller mounting and dismounting mechanism for Aerial Vehicles which remains safe in locked position even when motor rotates at high speed.
  • Another object of the present disclosure is to realize the quick dismounting of the propeller without any specialized tool.
  • aspects of the present disclosure relate to a quick mounting and dismounting mechanism for propellers in an Ariel Vehicle.
  • the present disclosure pertains to an improved locking and detaching mechanism for the propeller with the corresponding motor.
  • the disclosed propeller locking mechanism provides a simple, quick and secure mounting and dismounting technique; and in the process also improvesthe propeller locking system of the Aerial Vehicle by providing higher locking force at higher speeds thereby improving safety of the propeller.
  • the disclosed quick mounting and dismounting mechanism for propellers of Aerial Vehicle comprises a propeller mount; and a locking mechanism.
  • the locking mechanism comprises a set of at least two locking lever arms (also referred to as locking arms or arms or locking levers and all these terms used interchangeably hereinafter) attached to the propeller mount at corresponding pivot connections located around axis of the propeller mount.
  • the pivot connection divides the arms in two portions, namely an upper portion and a lower portion. End of the upper portion of the locking lever arms (referred hereinafter as locking end or alternately top end being located above the pivot connection)is adapted for engaging with propeller to hold the propeller in designated position.
  • the mechanism further incorporates one or more elastic members to provide locking force to the locking levers by biasing the pair of locking levers to their locking position.
  • the disclosed mechanism further includes means that provide additional locking force to the locking levers when propeller is moving at higher speeds.
  • the additional locking force is on account of centrifugal forces acting on lower portion of the locking levers.
  • outwardcentrifugal force acting on the lower portion of the locking lever arms provides inward locking force on the locking ends that engage with the propeller.
  • locking levers can be configured so that net centrifugal force is zero.
  • lower portions of the locking levers can be configured so that they provide equal centrifugal force, and the locking levers can be located at equispaced positions around axis of propeller mount, so that net centrifugal force is zero resulting in the rotor maintaining its balance without any unbalance mass.
  • the locking lever arms are rigid levers and comprise a protrusion at their locking ends /top ends (protruding end called hereinafter as locking jaw), a pivot connection, a lower portion extending from the pivot connection and a bottom end portion that is heavier than the remaining parts of the lever or/and located at a larger distance from axis of the propeller mount as compared to other parts of the locking lever arms.
  • the number of locking lever arms in the set of locking lever arms is restricted to two, and they are attached to propeller mount at corresponding pivot connections located at two diametrically opposite points about axis of the propeller mount, and the two locking lever arms are configured on the propeller mount such that a elastic member is interposed between the lower portions of the locking lever arms below the pivot junction, which provides outward bias to the lower portions of the locking lever arms, enabling the top ends of the locking lever arms to be forced inwards.
  • the elastic member biases the locking lever arms to be in a locked position as default.
  • the propeller for locking the propeller single-handedly with the motor, can be pushed onto the propeller mount from top through locking lever arms top end jaws.
  • the pushing force from the propeller deflects the top end jaw of the locking lever arms slightly outwards from its default locking position; the slight outward deflection of the locking lever jaws allow the propeller in and locks the propeller by trapping it between the locking lever top end jaws and the propeller mount.
  • the disclosed mechanism allows propeller to be quick-released from its locked position.
  • the quick-release mechanism requires pressing of lower portion of two locking lever arms, preferably by pushing bottom tip of the locking lever arms simultaneously, which compresses the elastic member between the locking lever arms and deflects the top jaw ends of the locking lever arms outwards, releasing the propeller from its locked position in the propeller mount.
  • use of two locking levers enables dismounting of the propeller by pressing the locking levers using single hand.
  • the motor of the Aerial Vehicle can be an in-runner or an out-runner motor, which may or may not have a motor can; thus the quick propeller locking mechanism may mount on to the motor drive shaft through a motor can or directly, thus incurring a mechanical contact for rotation.
  • the use of two locking lever arms and an elastic member provides a single-handed propeller quick mounting and dismounting mechanism, and at the same time improves locking safety of the propellers with the application of an additional clamping force on the upper portion of the locking lever arms induced by an outward centrifugal force due to rotating heavier lower portion of the locking lever arms, thereby improving the reliability of the locking mechanism.
  • the elastic member provided between two locking lever arms can be a bi-stable leaf spring that can keep the two locking lever arms in locking position and unlocking position, thereby doing away with need to hold lower portions of the two locking lever arms in inwardly pushed position while dismounting propeller.
  • the disclosure provides a simple and secure propeller mounting and dismounting mechanism with the effect of an equal and opposite force induced by a centrifugal force trapping the propeller in its locked position further against the conventional system of screws and movable buckle & elastic members to meet similar objectives
  • FIG.1 illustrates an exemplary isometric view showing assembly of a propeller to motor using the proposed mechanism in accordance with embodiments of the present disclosure.
  • FIG. 2 illustrates an exemplary exploded view of the disclosed quick mounting and dismounting mechanism for propellers in accordance with embodiments of the present disclosure.
  • FIG. 3 illustrates an exemplary schematic diagram of the disclosed locking arm lever in accordance with embodiments of the present disclosure.
  • FIGs. 4A and 4B illustrate exemplary schematic views of the disclosed quick mounting and dismounting mechanism for propellers showing its mounting parts in accordance with embodiments of the present disclosure.
  • FIG. 5 illustrates an exemplary side view of the disclosed quick mounting and dismounting mechanism showing unlocking position of locking lever arms in accordance with embodiments of the present disclosure.
  • FIG. 6 illustrates an exemplary representation of the proposed quick mounting and dismounting mechanism with bi-stable leaf spring between locking lever arms in accordance with an embodiment of the present disclosure.
  • Embodiments explained herein relate to a quick mounting and dismounting mechanism for propellers in an Ariel Vehicle.
  • embodiments of the present disclosure provide a mechanism comprising a pair of two pivoted locking lever arms pivotally attached to a propeller mount at two diametrically opposite points. The pivot point divides the locking lever arms between an upper portion and a lower portion. An elastic member between the two locking lever arms provides locking force to the pair of locking levers by biasing the pair of locking levers to their locking position.
  • Ends of the upper portions of the two locking lever arms (top ends or locking ends) work to hold the propeller under biasing force of the elastic member while other portion(lower portion) can be pushed inwards using a single hand against the biasing force of the elastic member to unlock the propeller for dismounting.
  • locking lever arms are configured such that a bottom end portion of lower portion of locking lever arms is heavier than the remaining parts of the lever or/and located at a larger distance from axis of the propeller mount as compared to other parts of the locking lever arms. Because of the heavier portion, lower portion when running at high speed, experiences outwardly acting centrifugal force that is transferred to top end as inwardly directed locking force on the top ends of upper portions to provide additional clamping force and additional safety.lt is to be appreciated that term locking lever arm has been used in the present disclosure to mean a rigid lever which is movable at a pivot junction or fulcrum.
  • the locking lever arms are rigid levers each of which comprises a small protruding end at top end that functions aslocking jaw, a pivot connection, a lower portion extending from the pivot connection and a bottom end portion heavier than the remaining parts of the lever.
  • the pivot connection of locking lever arms to the propeller mount is preferably at a point of the arm such that length of upper portion of the locking lever arms above the pivot junction is smaller in relation to the length of the lower portion of the locking lever arms.
  • the lower portion of the locking lever arms is the portion extending from the point of pivot junction to the tip of the bottom ends of the locking lever arms.
  • the tip of the bottom ends of the locking lever arms are shaped in a half-spheroid ball heavier than the remaining parts of the locking lever arms; wherein the weight of the lower portion of the locking lever arms become heavier than the upper portion of the locking lever arms.
  • the half-spheroid ball shaped bottom tips of the locking lever necessitates less effort by the user during dismounting of propeller using he disclosed quick-release mechanism.
  • the tip of the bottom ends of the locking lever arms are extended further in order to make the weight of the lower portion of the locking lever arms heavier than the upper portion of the locking lever arms.
  • the elastic member present between the locking lever arms can be a leaf spring with curved ends on which the lower portion of the locking lever arms rest.
  • elastic member between locking lever arms can be of any material providing an elastic mechanism, like a simple metal spring, rubber pad or any other such elastic part, which enables outward biasing of lower portion of the locking lever arms.
  • top end jaws of locking lever arms are wedge shaped having a inwardly sloping top surface so that when a propeller placed on the top end jaws of the locking lever arms and pushed down, the locking lever arms deflect outwards from ther default locking position, wherein the outward deflection of the locking lever arms allows the propeller to be moved in beyond the jaws to a locked position.
  • the locking lever arms can be designed in any suitable shape to generate centrifugal force and airflow conditions during the rotation of the motors for further improving the propeller performance.
  • the propeller can be quick-released from its locked position.
  • the quick-release mechanism requires the pressing of the bottom tip ends of the lower portion of the locking lever arms together which compresses the elastic member present between them and deflects the top jaw ends of the locking lever arms outwards, releasing the propeller from its locked position in the propeller mount.
  • the propeller mount comprises side plates, top plates, bottom plates and a central supporting part affixed between the top and bottom plates; all the parts are fastened with the help screws or nuts.
  • the propeller mount can be single part manufactured by injection molding etc.
  • the propeller mount may use a central supporting part for the mechanical connection of the propeller with the motor drive shaft.
  • the propeller may directly be fixed onto the motor drive shaft through the propeller mount for mechanical connection for the rotation of the propeller.
  • the motor of the Aerial Vehicle can be an in-runner or an out-runner motor, which may or may not have a motor can; thus the quick propeller locking mechanism may mount on to the motor drive shaft through a motor can or directly, thus incurring a mechanical contact for rotation.
  • a thin layer of elastic silicon is mounted in between the propeller mount and the propeller.
  • the propeller quick mounting dismounting mechanism is compatible with any propeller with high central hub thickness.
  • a packing part that compensates difference in thickness can be attached to the propeller center for locking it with the propeller locking structure.
  • the use of a pair of two locking lever arms and an elastic member provide a single-handed quick propeller mounting and dismounting mechanism and also improve the locking safety of the propellers with the application of an outward centrifugal force pertaining to the heavier lower portion of the locking lever arms, improving the reliability of the locking mechanism.
  • FIG.1 illustrates an exemplary isometric view showing assembly of a propeller to motor using the proposed mechanism in accordance with embodiments of the present disclosure.
  • the propeller connection structure comprises a propeller 104, locking mechanism 101 and propeller mount 105. Shown herein is the propeller 104 mounted in the propeller connection structure.
  • FIG. 2 illustrates an exemplary exploded view of the disclosed quick mounting and dismounting mechanism for propellers in accordance with embodiments of the present disclosure.
  • the propeller connection structure for an out-runner motor, and accordingly the propeller connection structure is mounted onto a motor can.
  • the propeller mount 105 comprises the side plates 202, atop plate 203, a central supporting part 204, a bottom plate 205 and a leaf-spring 201, all permanently fixed together with fixing hardware like screws.
  • the propeller mount 105 is fixed permanently onto the motor can 106 with the help of screws; wherein the motor can 106, the top plate 203 of the propeller mount, the bottom plate 205 of the propeller mount and the leaf-spring 201 all have a small spherical opening at the center point which are lined up concentrically along with the central supporting part 204 of the propeller mount placed between the top 203 and bottom plates 205 of the propeller mount for allowing motor drive shaft to pass through hand fit comfortably with the propeller for providing mechanical contact for propeller rotation.
  • the mechanical contact of the motor drive shaft with the propeller for propeller rotation is provided by the central support part 204.
  • the locking lever arms 102 pivotally connects to the propeller mount at either sides of the propeller mount for providing the locking mechanism of the propeller.
  • FIG. 3 illustrates an exemplary schematic diagram of the disclosed locking arm lever in accordance with embodiments of the present disclosure.
  • the locking lever arm 102 is a single rigid lever, comprising a upper portion 302 with a small protruding end at the top ends called the locking lever jaw 301, a pivot connection 303 providing the moment of the locking lever arms about a pivot line 306 in the propeller mount, a lower portion 304 extending from the pivot connection and a bottom end portion 305 heavier than the remaining parts of the lever.
  • the bottom end portion 305 is made heavier by providing a half-spheroid ball, so that when the mechanism is rotated at high speed about axis of the propeller mount, an outward acting centrifugal force acts on the lower portion 304 of the lever locking 102.
  • lever locking 102 is configured so that at least a part of the lower portion 304 and the half-spheroid ball is located farther from axis of the propeller mount to enhance the centrifugal force.
  • length and weight of the upper portion 302 of the locking lever arms 102 above the pivot junction 302 can be smaller in relation to the length and weight of the lower portion 304 of the locking lever arms 102. As can be appreciated it reduces effort required to push the lower portion 304 inwards, increases centrifugal force transferred to upper portion 302 thereby improving functioning of the mechanism.
  • FIGs. 4A and 4B illustrate exemplary schematic views of the disclosed quick mounting and dismounting mechanism for propellers showing its mounting parts in accordance with embodiments of the present disclosure.
  • Shown in FIG. 4A is the default locking position of the locking lever arms and the propeller connection structure; the propeller mount 101 with two locking lever arms 102 pivotally connected on either side of the propeller mount 101 such that leaf-spring 201 is interposed between the lower portion 304 of the locking lever arms below the pivot junction 303, which urges the lower portion 304 of the locking lever arms outwards, enabling the lever jaw ends 301 of the locking lever arms to deflect inwards and the lower portion 304 of the locking lever arms to deflect outwards and be in a locked position as default.
  • the propeller 104 for locking the propeller single-handedly with the motor, the propeller 104is pushed onto the propeller mount 105 from the top through the locking lever arms top end jaws 301 lining up concentrically with the protruding top of the central support part 204 of the propeller mount for mechanical contact with the motor.
  • the propeller 104 can comprise a small round packing part 103 for fixing it into the propeller mount 105 when the thickness of the center of the propeller 104 is less than the thickness for which the disclosed device is configured.
  • the packing part 103 can have thickness that compensates the difference in thickness.
  • force induced from the propeller 104when pushed inwards deflects the top end jaw 301 of the locking lever arms slightly outwards from its default locking position.
  • the slight outward deflection of the locking lever jaws 301 allows the propeller in and locks the propeller by trapping it between the locking lever top end jaws 301 and the propeller mount 105.
  • the locking mechanism is secured further by the application of an equal and opposite force induced on the locking lever arm's upper portion 302, specifically at top jaw ends 301 due to an outward centrifugal force that acts upon the heavier bottom ends 305 of the locking lever arm 102.
  • the heavier weight of the lower portion 304 of the locking lever arms enables an outward centrifugal force to act upon it which deflects the lower portion 304 of the locking lever arms 102 further away from its resting position over the elastic member 201, which in turn imposes an opposite inward force on the top locking lever jaws 301 which further tightly grips the propeller 104 between the locking lever jaw ends 301 and the propeller mount 105.
  • the locking lever arms 102 can be designedin any suitable shape to generate centrifugal force so that airflow conditions are not compromised duringthe rotation of the propeller /motor.
  • FIG. 5 illustrates an exemplary side view of the disclosed quick mounting and dismounting mechanism showing unlocking position of locking lever arms in accordance with embodiments of the present disclosure.
  • the propeller can be quick-released from its locked position.
  • the quick-release mechanism requires the pressing of the lower portion 304 such as the bottom tip ends 305 of the locking lever arms 102 together which compresses the elastic member 201 present between them and deflects the top jaw ends 301 of the locking lever arms outwards, releasing the propeller from its locked position in the propeller mount.
  • propeller 104 can be mounted/ dismounted.
  • the elastic member 201 present between them expands again and the locking lever arms 102 return to their original locked position.
  • the disclosed quick-release mechanism can be configured to prevent holding of the bottom tip ends 305 of the locking lever arms 102 in pressed position while the propeller is being mounted/ dismounted. This can be done by providing two stable positions for the locking lever arms 102 - one when it is pressed inwards (i.e. unlocked position of the locking lever arms 102) and other when they are pulled outwards (i.e. locked position of the locking lever arms 102). For this, as shown in FIG.
  • elastic member interposed between the lower portions of the locking lever arms 102 can be a bi-stable leaf-spring 601 that can take two stable positions such as a first stable position 602 and a second stable position 603, which provides a default outward bias to the top ends of the locking lever arms 102 at a first stable position 602 and an inward position of the top ends of the locking lever arms 102 at a second stable position 603.
  • the propeller for locking the propeller single-handedly with the motor, can be pushed over the first stable position of the bi-stable leaf-spring 601 from top through the outward biased locking lever arm's top ends to the second stable position of the bistable leaf-spring; the alteration of the first stable position of the bi-stable leaf-spring to the second stable position 603 allows the propeller in and moves the locking lever arms top end's position from default outward bias to an inward position locking the propeller better by trapping it between the locking lever top end jaws and the propeller mount.
  • the alternate embodiment provides the advantage of exerting only a slight pushing force to alter the first stable position 602 of the bi-stable leaf-spring 601 to the second stable position 603 to lock the propeller rather than deflecting the top end jaws of the locking lever arms to lock the propeller with the motor shaft.
  • the disclosed mechanism allows propeller to be quick-released from its locked position.
  • the quick-release mechanism requires pressing of lower portion 304 of two locking lever arms 102, preferably by pushing the bottom tip ends 305 of the locking lever arms 102 simultaneously, which alters the second stable position 603 of the bi-stable leaf-spring 601 to the first stable position 602 deflecting the top jaw ends 301 of the locking lever arms 102 outwards, releasing the propeller from its locked position in the propeller mount.
  • the present disclosure provides a propeller quick mounting and dismounting mechanism for an Ariel Vehicle which pertains to an improved locking and detaching mechanism for the propeller with the motor.
  • the disclosed propeller locking mechanism provides a simple, quick and secure mounting and dismounting technique; and in the process also improves the propeller locking system of the Aerial Vehicle by application of outward centrifugal force acting on the locking lever arms.
  • the present disclosure simplifies attaching/detaching a propeller of an Aerial Vehicle such as an UAV, with motor.
  • the present disclosure provides a simple, quick mounting and dismounting, cost effective and secure mechanism for propeller mounting in an Aerial Vehicles.
  • the present disclosure provides a single-handedly locking/detaching mechanism for quick mounting and dismounting of a propeller for Aerial Vehicles.
  • the present disclosure provides a quick propeller mounting and dismounting mechanism for Aerial Vehicles which remains safe in locked position even when motor rotates at high speed.
  • the present disclosure realizes quick dismounting of the propeller without any specialized tool.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un mécanisme qui permet de monter et de démonter rapidement une hélice, ainsi qu'un démontage à une seule main. Le mécanisme comprend un support d'hélice, un ensemble d'au moins deux leviers de verrouillage (102) fixés de manière pivotante au support d'hélice. Un ou plusieurs éléments élastiques (201) maintiennent les leviers de verrouillage (102) en position de verrouillage. Une partie du levier de verrouillage au-dessus du point de pivotement est en forme de mâchoire afin de maintenir l'hélice en position, et une partie du levier de verrouillage au-dessous du point de pivotement est pressée vers l'intérieur afin de déverrouiller l'hélice. La partie inférieure du levier de verrouillage est plus lourde et est positionnée plus loin par rapport à l'axe de rotation, de telle sorte que lorsque le mécanisme tourne à grande vitesse, la partie inférieure subit une force centrifuge qui est transférée à la partie au-dessus du point de pivotement afin de fournir une force de verrouillage supplémentaire pour maintenir les leviers de verrouillage (102) dans la position de verrouillage. Dans un mode de réalisation, le mécanisme comprend deux leviers de verrouillage (102) qui peuvent être poussés d'une seule main pour séparer l'hélice des leviers de verrouillage.
PCT/IB2018/058184 2017-10-25 2018-10-22 Mécanisme à une seule main de montage et de démontage rapide d'une hélice Ceased WO2019082044A1 (fr)

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IN201721037829 2017-10-25

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Cited By (4)

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Publication number Priority date Publication date Assignee Title
CN111655579A (zh) * 2019-05-17 2020-09-11 深圳市大疆创新科技有限公司 快拆连接组件、动力组件、动力套装以及无人机
CN113353255A (zh) * 2021-05-31 2021-09-07 四川省天域航通科技有限公司 一种无人机桨叶的快速拆装装置
CN114514175A (zh) * 2019-10-29 2022-05-17 深圳市大疆创新科技有限公司 旋翼安装组件
US12459618B2 (en) 2021-12-22 2025-11-04 Navico, Inc. Device for steering a trolling motor and method of the same

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CN205837188U (zh) * 2016-07-15 2016-12-28 浙江大学 一种农用多旋翼无人机桨叶固定机构
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

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Publication number Priority date Publication date Assignee Title
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
CN205837188U (zh) * 2016-07-15 2016-12-28 浙江大学 一种农用多旋翼无人机桨叶固定机构

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111655579A (zh) * 2019-05-17 2020-09-11 深圳市大疆创新科技有限公司 快拆连接组件、动力组件、动力套装以及无人机
CN114514175A (zh) * 2019-10-29 2022-05-17 深圳市大疆创新科技有限公司 旋翼安装组件
US12162593B2 (en) 2019-10-29 2024-12-10 SZ DJI Technology Co., Ltd. Rotor mount assembly
CN113353255A (zh) * 2021-05-31 2021-09-07 四川省天域航通科技有限公司 一种无人机桨叶的快速拆装装置
CN113353255B (zh) * 2021-05-31 2023-04-18 四川省天域航通科技有限公司 一种无人机桨叶的快速拆装装置
US12459618B2 (en) 2021-12-22 2025-11-04 Navico, Inc. Device for steering a trolling motor and method of the same

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