WO2018058328A1 - 螺旋桨保护罩及使用该螺旋桨保护罩的无人机 - Google Patents

螺旋桨保护罩及使用该螺旋桨保护罩的无人机 Download PDF

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Publication number
WO2018058328A1
WO2018058328A1 PCT/CN2016/100433 CN2016100433W WO2018058328A1 WO 2018058328 A1 WO2018058328 A1 WO 2018058328A1 CN 2016100433 W CN2016100433 W CN 2016100433W WO 2018058328 A1 WO2018058328 A1 WO 2018058328A1
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WO
WIPO (PCT)
Prior art keywords
propeller
protection cover
sleeve
cover according
holding member
Prior art date
Application number
PCT/CN2016/100433
Other languages
English (en)
French (fr)
Inventor
徐暉
唐尹
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 PCT/CN2016/100433 priority Critical patent/WO2018058328A1/zh
Priority to CN201680005188.6A priority patent/CN107466282B/zh
Publication of WO2018058328A1 publication Critical patent/WO2018058328A1/zh

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Classifications

    • 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
    • B64U30/299—Rotor guards
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • 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
    • B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors

Definitions

  • the invention relates to the technical field of drone safety, in particular to a propeller protection cover and a drone using the propeller protection cover.
  • a drone is a non-manned tool that is operated by a radio remote control device or remote control device to perform a task.
  • Navigational flight control systems, program control devices, and power supply equipment are installed on general UAVs.
  • UAVs have been developed and applied in many fields, especially in general industrial and military research. Military significance and economic status.
  • the drone usually includes a fuselage and an arm extending from the fuselage, each of which is provided with a propeller, and the rotation of the propeller drives the drone to fly.
  • a propeller usually includes a fuselage and an arm extending from the fuselage, each of which is provided with a propeller, and the rotation of the propeller drives the drone to fly.
  • the high speed rotation of the propeller may hit the hard object and cause the propeller to be damaged, or the propeller may scratch people or objects, so it is necessary to design a propeller protection cover.
  • the existing propeller cover can provide limited protection and is not easy to disassemble.
  • a propeller protection cover the propeller protection cover includes a protection bracket, the propeller protection cover further includes a latching mechanism disposed on the protection bracket, the latching mechanism being detachably mounted to the arm of the drone The latching mechanism surrounds the arm to enable the latching mechanism to be sleeved on the arm.
  • An unmanned aerial vehicle includes a plurality of arms and a plurality of propeller assemblies including a fuselage and the fuselage, the drone further comprising a propeller guard as described above, the latching mechanism being disposed at The arm is located between the and the propeller assembly.
  • the propeller cover and the drone described above provide advantageous protection and are easy to disassemble.
  • FIG. 1 is a top plan view of a propeller protection cover for a drone according to an embodiment of the present invention.
  • FIG. 2 is a perspective view of a propeller protection cover for a drone according to an embodiment of the present invention.
  • FIG 3 is an exploded view of a lock structure of a propeller protection cover for a drone according to an embodiment of the present invention.
  • FIG. 4 is a partial perspective view of the propeller protection cover of the unmanned aerial vehicle in an unlocked state according to an embodiment of the present invention.
  • Figure 5 is a perspective view of the propeller cover shown in Figure 4 from another perspective.
  • FIG. 6 is a partial perspective view of a propeller protection cover of a drone according to an embodiment of the present invention in a locked state.
  • Figure 7 is a perspective view of the propeller cover shown in Figure 6 from another perspective.
  • FIG. 8 is an unmanned aerial vehicle equipped with a propeller protection cover according to an embodiment of the present invention.
  • Drone 1 Propeller cover 10 Protective bracket 100 Radial bracket 1000 Curved bracket 1002 Mount 102 Lock mechanism 103 Card holder 104 Bottom plate 1040 Clamping groove 1041 Clamping wall 1042 Second sleeve 1046 Second sleeve hole 10460 First bushing 1043 Rib reinforcement 10430 First shaft 105 First holding member 106 First holder body 1060 First through hole 1062 Third bushing 1064 Third sleeve hole 10640 First buckle 1066 Second shaft 107 Locking piece 108 Fourth sleeve hole 1080 Fifth sleeve hole 1082 Third axis 109 Second holding member 110 Second holding body 1100 Second through hole 1102 Sixth sleeve hole 1104 Second buckle 1106 body 12 Arm 14 Power mechanism 16
  • a component when referred to as being “fixed” to another component, it can be directly on the other component or the component can be present.
  • a component When a component is considered to "connect” another component, it can be directly connected to another component or possibly a central component.
  • a component When a component is considered to be “set to” another component, it can be placed directly on another component or possibly with a centered component.
  • the terms “vertical,” “horizontal,” “left,” “right,” and the like, as used herein, are for illustrative purposes only.
  • a propeller protection cover 10 includes a protection bracket 100 , a mounting base 102 disposed on the protection bracket 100 , and the mount Connected latch mechanism 103.
  • the protective bracket 100 has a substantially fan-shaped structure, and includes a radial bracket 1000 and an arc bracket 1002 connecting the radial bracket 1000.
  • the number of the radial brackets 1000 is two. In other embodiments, the number of the radial brackets 1000 may also be one, three, four, five, etc. Design needs prevail.
  • the two radial brackets 1000 are connected to the curved bracket 1002 at one end and to the mounting base 102 at the other end.
  • the mounting base 102 is substantially circular and includes a mounting slot and a through hole 1020 formed at a bottom of the mounting slot for carrying a power device such as a propeller and a motor thereof; the through hole 1020 is for providing no The stand of the human machine arm is worn and the weight of the propeller cover 10 can be reduced.
  • the mounting seat 102 is located at a center of the arc-shaped bracket 1002, and a center of the arc-shaped bracket 1002 substantially coincides with a center of rotation of the blade of the propeller, that is, a circle where the arc-shaped bracket is located and The circle in which the rotating surface of the blade of the propeller (i.e., the range scanned when the blade is rotated) is concentric, the diameter of the circle of the former being larger than the diameter of the circle of the latter, so that the protective bracket 100 can provide the propeller protection.
  • the latch mechanism 103 extends from the mounting base 102 toward a side away from the protection bracket 100.
  • the latch mechanism 103 includes a latching seat 104, a first latching member 106 rotatably coupled to the latching seat 104, and a latching member 108 rotatably coupled to the other side of the latching seat 104. And a second holding member 110 connected to an end of the locking member 108 away from the holding seat 104.
  • the retaining seat 104 includes a bottom plate 1040 extending from a periphery of the mounting seat, and two clamping walls 1042 extending from opposite sides of the bottom plate 1040 away from the bottom plate 1040.
  • the two clamping walls 1042 and the bottom plate 1040 together define a U-shaped clamping groove 1041.
  • the U-shaped clamping groove 1041 is for holding the arm therein.
  • a first sleeve 1043 is disposed on a side of the two clamping walls 1042 facing away from the clamping groove 1041.
  • the number of the first bushings 1043 is two.
  • the first sleeves 1043 are arranged side by side and in parallel.
  • the first sleeve 1043 is configured to mount the first holder 106.
  • a second sleeve 1046 is disposed on a side of the two clamping walls 1042 facing away from the clamping groove 1041.
  • the number of the second sleeves 1046 is two.
  • the two second sleeves 1046 are arranged side by side and in parallel.
  • Each of the second sleeves 1046 is provided with a second sleeve hole 10460.
  • the second sleeve hole 10460 is used to mount the locking member 108.
  • the first holder member 106 includes a first holder body 1060, a third sleeve 1064 disposed at one end of the first holder body 1060, and a first holder body 1060 disposed on the first holder body 1060.
  • the first fastening portion 1066 on the opposite side of the third sleeve 1064 is described.
  • the first holder body 1060 has a substantially square shape with a first through hole 1062 therebetween.
  • the first through hole 1062 has a square shape. It can be understood that in other embodiments, the shape of the first through hole may be any other suitable shape, such as a circle, a star, or the like.
  • the number of the third sleeves 1064 is three, and the three third sleeves 1064 are arranged in parallel, and each of the third sleeves 1064 is provided with a third sleeve hole 10640.
  • the three first sleeves 1064 sandwich the two first sleeves 1043 therebetween, and the sleeve holes of the first sleeve 1043 are corresponding to the third sleeve holes 10640 so that a first shaft
  • the 105 can be inserted therein to rotationally connect the first holder 106 to the holder 104.
  • the third sleeve 1064 can also be an integral sleeve disposed between the two first sleeves 1043.
  • the third sleeve 1064 may also include two spaced portions, and the first sleeves 1043 are spanned between the two portions. At this time, the first sleeve 1043 is also Can be a whole sleeve.
  • the first sleeve 1043 extends along the surface of the second clamping wall to form a reinforcing rib 10430 (see FIG. 5).
  • the locking member 108 is connected to the second sleeve 1046 at one end and to the second holding member 110 at the other end.
  • One end of the locking member 108 is interposed between the two second sleeves 1046, and one end of the locking member 108 is provided with a fourth sleeve hole 1080, the fourth sleeve hole 1080 and the first
  • the second sleeve hole 10460 of the second sleeve 1046 corresponds to the second sleeve hole 10460.
  • the second rotating shaft 107 can respectively pass through the second sleeve hole 10460 and the fourth sleeve hole 1080 to rotatably connect the locking member 108 and the holding seat 104.
  • the other end (free end) of the locking member 108 is provided with a fifth sleeve hole 1082.
  • the second clamping member 110 is provided with a sixth sleeve hole 1104 corresponding to the fifth sleeve hole 1082, and the third rotating shaft 109 can respectively pass through the fifth sleeve hole 1082 and the sixth sleeve hole 1104.
  • the second holding member 110 and the locking member 108 are connected.
  • the second holder 110 includes a second holder body 1100 and a second fastening portion 1106 disposed on a side of the second holder body away from the sixth sleeve hole 1104.
  • the second fastening portion 1106 can be engaged with the first fastening portion 1066.
  • a second through hole 1102 is defined in the middle of the second holding body 1100. The locking member 108 and the second sleeve 1046 can be received in the second through hole 1102.
  • the third sleeve 1064 of the first holding member 106 is first disposed to cross the first sleeve 1043 to sandwich the first sleeve 1043 on the third sleeve 1064.
  • the first sleeve hole of the first sleeve 1043 corresponds to the third sleeve hole 10640 of the third sleeve 1064, and then the first rotating shaft 105 is respectively passed through the The first sleeve hole of the first sleeve 1043 and the third sleeve hole 10640 of the third sleeve 1064 complete the installation of the first holder 106.
  • the locking member 108 is then sandwiched between the second sleeves 1046, and the second sleeve hole 10460 is corresponding to the fourth sleeve hole 1080, and then the second shaft is rotated.
  • the locking member 108 is completed by passing through the second sleeve hole 10460 and the fourth sleeve hole 1080 respectively.
  • one end of the second holding member 110 is sleeved on one end of the fifth sleeve hole 1082 of the locking member 108, and the fifth sleeve hole 1082 and the sixth sleeve are The hole 1104 corresponds to, and then the third rotating shaft 109 is respectively passed through the fifth sleeve hole 1082 and the sixth sleeve hole 1104 to complete the installation of the second holder 110.
  • the installation Please refer to Figure 4 and Figure 5 for the installation.
  • the state shown in FIGS. 4 and 5 is a view in which the latch mechanism 103 is in an unlocked state.
  • the unlocked state the first latching portion 1066 of the first latching member 106 and the second latching portion 1106 of the second latching member 110 are not snapped together. At this time, it is possible to facilitate the insertion of the arm into the holding groove 1041.
  • the first holding member 106 When the arm is placed in the clamping groove 1041, the first holding member 106 is rotated in the direction of the second holding member 110, and the second holding member 110 is facing the first The direction of the holding member 106 is rotated, and the locking member 108 is rotated in a direction away from the bottom plate 1040 of the holding seat 104, so that the second locking portion 1106 of the second holding member 110 can The first hooking portion 1066 of the first retaining member 106 is engaged.
  • the locking member 108 is then pressed down such that the locking member 108 rotates in the direction of the bottom plate 1040 of the holder 104, and when rotated to a designated position, for example, the locking member 108 is attached to the
  • the second holding member 110 is subjected to a downward pulling force to be tightly engaged with the first holding member 106.
  • the first holding member 106 is subjected to a lateral pulling force of the second holding member 110 such that the two clamping walls 1042 are adjacent to each other to tightly fix the arm in the clamping groove 1041.
  • 6 and 7 are views showing the latch mechanism 103 in a locked state, in which the arm is not inserted.
  • the propeller guard 10 can be used in a drone that can be used in any suitable environment, such as in the air (eg, a rotorcraft, a fixed-wing aircraft, or a fixed-wing and rotor-mixed aircraft), in water (eg, Boat or submarine), on the ground (eg, motorcycle, car, truck, bus, train, etc.), in space (eg, space shuttle, satellite or detector), or underground (eg subway), or above Any combination of environments.
  • the drone is a rotorcraft, wherein the rotors may be a single rotor, a double rotor, a triple rotor, a quadrotor, a six-rotor, and an eight-rotor.
  • the drone in the following embodiment is described by taking a quadrotor as an example.
  • FIG. 8 shows an unmanned aerial vehicle 1 including the propeller protection cover 10 according to an embodiment of the present invention.
  • the drone 1 includes a fuselage 12 and a plurality of arms 14 extending from the fuselage 12. Each end of the arm is held away from the end of the body 12 in the U-shaped clamping groove 1041 of the latch mechanism 103 of the propeller guard 10.
  • the mount 102 of the propeller cover 10 is used to mount the power mechanism 16.
  • a power mechanism mounting portion is opened at a distal end portion of the arm 14 , and the power mechanism mounting portion corresponds to the mounting base 102 .
  • the power mechanism 16 can connect the arm 14 and the propeller guard 10 together by the power mechanism mounting portion and the mounting base 102.
  • the power mechanism 16 may include a motor mounted on a power mechanism mounting portion of the arm, the rotating shaft of the motor being coupled to a propeller.
  • the power mechanism 16 can include one or more of a rotor, a propeller, a blade, an engine, a motor, a wheel set, a shaft, a magnet, or a nozzle.
  • the drone 1 may include one, two, three, four or more power mechanisms.
  • the power mechanisms 16 can be of the same type. Alternatively, the one or more power mechanisms can be different types of power mechanisms.
  • the power mechanism 16 can cause the drone 1 to take off vertically from a surface or land vertically on a surface without requiring the drone to make any horizontal movement (eg, no Need to slide on the runway).
  • the drone 1 can be used to operate to cause the drone 1 to hover over a specified position and orientation.
  • the drone 1 can include a plurality of horizontally-oriented rotors that provide lift and thrust for the drone.
  • the plurality of horizontally-oriented rotors can be actuated to provide vertical takeoff, vertical landing, hovering capability to the drone 1 .
  • one or more horizontally-oriented rotors can be rotated clockwise while one or more horizontal rotors are rotatable counterclockwise.
  • the number of rotors that rotate clockwise can be equal to the number of rotors that rotate counterclockwise.
  • each horizontal steering rotor can be varied independently to control the lifting force and/or thrust generated by the rotor to adjust the spatial orientation, velocity, and/or acceleration of the drone 1 (eg, relative to three-dimensional translation) Degree of freedom and three-dimensional rotational freedom).
  • the drone 1 may include other suitable number of arms, such as six, eight, and the like.
  • Two adjacent propeller guards can be connected by a connecting structure 11 (as shown in Figure 1), and the propeller guards connected together have greater impact resistance. It can be understood that in other embodiments, the two propeller guards 10 can also be integrally formed as one piece. In some embodiments, two adjacent propeller guards 10 on the same side of the fuselage 12 can be connected together by a quick release self-locking mechanism, which is easy to install when used, and can be easily disassembled and stored during storage. In some embodiments, the two propeller guards 10 on the same side of the fuselage 12 can also be connected together by a foldable connecting device that can be deployed to the state shown in Figure 8 when in use, when needed for storage. , can be folded and overlapped for easy storage.
  • the components such as the buckle and the rotating shaft of the locking mechanism of the arm 14 can withstand a large impact force (for example, a collision occurs at a speed of 6 m/s), thereby protecting the propeller. Suffering or being less damaged, as well as protecting the foreign object from the rotation of the propeller.
  • the shape of the clamping groove 1041 surrounded by the bottom plate 1040 and the clamping wall 1042 is not limited to a U shape, and the shape of the clamping groove 1041 can be adaptively changed according to the shape of the arm.
  • the shape of the clamping groove 1041 may be an open elliptical shape.
  • the manner of fixing the first latching portion 1066 of the first latching member 106 and the second latching portion 1106 of the second latching member 110 is not limited to the hooking manner shown in the figure.
  • any suitable detachable fixing method such as a card slot and a hook, a buckle and a locking tongue, and the like.
  • the first retaining member 106 is centrally provided with a first through hole 1062 to provide buffer for the first retaining member 106 to be impacted.
  • the first through hole 1062 may be omitted, and the body of the first holding member 106 is a complete piece.
  • first rotating shaft 105 and the first holding member 106 can be integrally formed or fixed together by other means; in other embodiments, the first rotating shaft 105 can also be combined with the clip.
  • the retaining wall 1042 is integrally formed or fixed together, and the first retaining member 106 can be detachably coupled to the first rotating shaft 105.
  • the second rotating shaft 107 and the clamping wall 1042 can be integrally formed or fixed together, and the locking member 108 can be separately connected to the second rotating shaft 107.
  • the second rotating shaft 107 can also be integrally formed or fixed together with the locking member 108.
  • the third rotating shaft 109 can also be integrally formed or fixed together with the locking member 108.
  • the third rotating shaft 109 can also be integrally formed or fixed with the second holding member 110, and the locking member 108 can be separately connected to the third rotating shaft 109. .
  • mount 102 can be omitted, and the power mechanism does not need to be carried on the mount.
  • the locking member 108 can be omitted, and the second holding member 110 can be directly rotatably connected to the outer side wall of the holding base 104 away from the first holding member 106.
  • the first holder 106 and the second holder 110 can be separately fixed together.
  • the locking member 108 and the second holding member 110 can be omitted.
  • the first holding member 106 can be directly engaged with the clamping arm of the holding seat 106. Combine and separate.

Abstract

一种螺旋桨保护罩（10），所述螺旋桨保护罩包括保护支架（100），所述螺旋桨保护罩还包括设置在所述保护支架上的卡锁机构（103），所述卡锁机构能够分离地安装于无人机的机臂（14）上，所述卡锁机构环绕所述机臂以使所述卡锁机构能够套设在所述机臂上。

Description

螺旋桨保护罩及使用该螺旋桨保护罩的无人机 技术领域
本发明涉及无人机安全技术领域，尤其是一种螺旋桨保护罩及使用该螺旋桨保护罩的无人机。
背景技术
无人机是一种由无线电遥控设备或者远程控制装置操纵以执行任务的非载人工具。一般的无人机上都会安装有导航飞行控制系统、程序控制装置和电源设备等，近些年来，无人飞行器在多个领域得到发展和应用，尤其是一般工业和军事研究的热点，具有重大的军事意义和经济地位。
无人机通常包括机身及自所述机身伸展的机臂，每一机臂上设置有螺旋桨，螺旋桨的旋转带动所述无人机飞行。但是有时候由于操控失误或所述无人机失控，螺旋桨高速旋转可能会磕碰硬物导致螺旋桨损坏，或是螺旋桨划伤人或物，因此有必要设计一种螺旋桨保护罩。
目前现有的螺旋桨保护罩能提供的防护程度有限，且拆装不易。
发明内容
有鉴于此，有必要提供一种能提供有利防护且便于拆装的螺旋桨保护罩。
一种螺旋桨保护罩，所述螺旋桨保护罩包括保护支架，所述螺旋桨保护罩还包括设置在所述保护支架上的卡锁机构，所述卡锁机构能够分离地安装于无人机的机臂上，所述卡锁机构环绕所述机臂以使所述卡锁机构能够套设在所述机臂上。
一种无人机，包括包括机身、与所述机身连接的多个机臂及多个螺旋桨组件，所述无人机还包括上所述的螺旋桨保护罩，所述卡锁机构设置在所述机臂上并位于所述和所述螺旋桨组件之间。
上所述螺旋桨保护罩及无人机，能提供有利防护且便于拆装。
 附图说明
图1是本发明实施方式提供的一种无人机的螺旋桨保护罩的俯视图。
图2是本发明实施方式提供的一种无人机的螺旋桨保护罩的立体图。
图3是本发明实施方式提供的一种无人机的螺旋桨保护罩的锁扣结构的分解图。
图4是本发明实施方式提供的一种无人机的螺旋桨保护罩处于解锁状态的局部立体图。
图5是图4所示的螺旋桨保护罩另一视角的立体图。
图6是本发明实施方式提供的一种无人机的螺旋桨保护罩处于锁扣状态的局部立体图。
图7是图6所示的螺旋桨保护罩另一视角的立体图。
图8是本发明实施方式提供的一种安装有螺旋桨保护罩的无人机。
主要元件符号说明
无人机 1
螺旋桨保护罩 10
保护支架 100
径向支架 1000
弧形支架 1002
安装座 102
卡锁机构 103
卡持座 104
底板 1040
夹持槽 1041
夹持壁 1042
第二轴套 1046
第二轴套孔 10460
第一轴套 1043
加强肋 10430
第一转轴 105
第一卡持件 106
第一卡持件本体 1060
第一通孔 1062
第三轴套 1064
第三轴套孔 10640
第一卡扣部 1066
第二转轴 107
锁扣件 108
第四轴套孔 1080
第五轴套孔 1082
第三转轴 109
第二卡持件 110
第二卡持件本体 1100
第二通孔 1102
第六轴套孔 1104
第二卡扣部 1106
机身 12
机臂 14
动力机构 16
如下具体实施方式将结合上述附图进一步说明本发明。
具体实施方式
下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行清楚、完整地描述，显然，所描述的实施例仅仅是本发明一部分实施例，而不是全部的实施例。基于本发明中的实施例，本领域普通技术人员在没有做出创造性劳动前提下所获得的所有其他实施例，都属于本发明保护的范围。
需要说明的是，当组件被称为“固定于”另一个组件，它可以直接在另一个组件上或者也可以存在居中的组件。当一个组件被认为是“连接”另一个组件，它可以是直接连接到另一个组件或者可能同时存在居中组件。当一个组件被认为是“设置于”另一个组件，它可以是直接设置在另一个组件上或者可能同时存在居中组件。本文所使用的术语“垂直的”、“水平的”、“左”、“右”以及类似的表述只是为了说明的目的。
除非另有定义，本文所使用的所有的技术和科学术语与属于本发明的技术领域的技术人员通常理解的含义相同。本文中在本发明的说明书中所使用的术语只是为了描述具体的实施例的目的，不是旨在于限制本发明。本文所使用的术语“及／或”包括一个或多个相关的所列项目的任意的和所有的组合。
下面结合附图，对本发明的一些实施方式作详细说明。在不冲突的情况下，下述的实施例及实施例中的特征可以相互组合。
请参阅图1，图1示出了本发明实施例的一种螺旋桨保护罩，所述螺旋桨保护罩10包括保护支架100、设置在所述保护支架100上的安装座102及与所述安装座连接的卡锁机构103。其中所述保护支架100大致呈扇形结构，包括径向支架1000及连接所述径向支架1000的弧形支架1002。在本实施例中，所述径向支架1000的数量为两根，在其他实施例中，所述径向支架1000的数量也可以为一根、三根、四根、五根等等，以实际设计需求为准。所述两根径向支架1000一端连接于所述弧形支架1002，另一端连接于所述安装座102。所述安装座102大致呈圆形，包括有安装槽和开设在安装槽底部的通孔1020，所述安装槽用于承载动力装置，例如螺旋桨及其电机；所述通孔1020用于供无人机机臂的脚架穿设，且可以减轻所述螺旋桨保护罩10的重量。所述安装座102位于所述弧形支架1002的圆心位置处，所述弧形支架1002的圆心与所述螺旋桨的叶片的旋转中心大致重合，也即所述弧形支架所在的圆与所述螺旋桨的叶片的旋转面（即所述叶片转动时所扫描的范围）所在的圆为同心圆，前者的圆的直径大于后者的圆的直径，从而所述保护支架100能够为所述螺旋桨提供保护。
请同时参阅图2及图3所示，所述卡锁机构103自所述安装座102向远离所述保护支架100的一侧延伸。所述卡锁机构103包括卡持座104，转动地连接在所述卡持座104上的第一卡持件106，转动地连接在所述卡持座104上另一侧的锁扣件108，及连接在所述锁扣件108远离所述卡持座104的一端的第二卡持件110。
所述卡持座104包括自所述安装座周缘延伸出来的底板1040，及自所述底板1040两相对侧向远离所述底板1040的方向延伸的两夹持壁1042。两所述夹持壁1042及所述底板1040共同围设一U形夹持槽1041。所述U形夹持槽1041用于夹持机臂于其内。
两所述夹持壁1042中的第一夹持壁背离所述夹持槽1041的一侧设置有第一轴套1043。在本实施例中，所述第一轴套1043的数量为两个。两所述第一轴套1043并排且平行间隔设置。所述第一轴套1043用于装设所述第一卡持件106。
两所述夹持壁1042中的第二夹持壁背离所述夹持槽1041的一侧设置有第二轴套1046，在本实施例中，所述第二轴套1046的数量为两个。两所述第二轴套1046并排且平行间隔设置。每一第二轴套1046均设置有第二轴套孔10460。所述第二轴套孔10460用于装设所述锁扣件108。
所述第一卡持件106包括第一卡持件本体1060、设置在所述第一卡持件本体1060一端的第三轴套1064及设置在所述第一卡持件本体1060上与所述第三轴套1064相背的一侧上的第一卡扣部1066。所述第一卡持件本体1060大致呈方形，其中间开设有第一通孔1062。所述第一通孔1062呈方形，可以理解的是，在其他实施例中，所述第一通孔的形状可以为其他任意适宜的形状，例如圆形、星形等。所述第三轴套1064数量为三个，三个所述第三轴套1064平行间隔设置，每一所述第三轴套1064均设置有第三轴套孔10640。三个所述第三轴套1064将两所述第一轴套1043夹设在其间，所述第一轴套1043的轴套孔与第三轴套孔10640对应设置，以使得一第一转轴105能插设其中，从而将所述第一卡持件106转动连接在所述卡持座104上。
可以理解的是，在其他实施例中，所述第三轴套1064也可以为一个整体的轴套，夹设在两所述第一轴套1043之间。在其他实施例中，所述第三轴套1064也可以包括间隔设置的两部分，两所述第一轴套1043架设在所述两部分之间，此时，所述第一轴套1043也可以为一个整体的轴套。
在图所示的实施例中，为了进一步增加轴套的稳固性，所述第一轴套1043沿着所述第二夹持壁表面延伸形成加强肋10430（请参阅图5所示）。
所述锁扣件108一端连接于所述第二轴套1046，另一端连接于所述第二卡持件110。所述锁扣件108的一端夹设在两所述第二轴套1046之间，所述锁扣件108一端设置有第四轴套孔1080，所述第四轴套孔1080与所述第二轴套1046的第二轴套孔10460对应。第二转轴107能够分别穿设所述第二轴套孔10460及所述第四轴套孔1080而转动连接所述锁扣件108与所述卡持座104。
所述锁扣件108另一端（自由端）设有第五轴套孔1082。所述第二卡持件110对应该第五轴套孔1082设置有第六轴套孔1104，第三转轴109能够分别穿设所述第五轴套孔1082及第六轴套孔1104二转动连接所述第二卡持件110与所述锁扣件108。
所述第二卡持件110包括第二卡持件本体1100及设置在所述第二卡持件本体上远离所述第六轴套孔1104的一侧的第二卡扣部1106。所述第二卡扣部1106能够与所述第一卡扣部1066相扣合。所述第二卡持件本体1100中间开设有第二通孔1102，所述锁扣件108及所述第二轴套1046能够容设在所述第二通孔1102中。
组装时，可先将所述第一卡持件106的第三轴套1064与所述第一轴套1043交叉设置以将所述第一轴套1043夹设在所述第三轴套1064的三部分之间，并使得所述第一轴套1043的第一轴套孔与所述第三轴套1064的第三轴套孔10640对应，然后将所述第一转轴105分别穿设所述第一轴套1043的第一轴套孔与所述第三轴套1064的第三轴套孔10640，完成第一卡持件106的安装。然后将所述锁扣件108夹设在所述第二轴套1046之间，并使得所述第二轴套孔10460与所述第第四轴套孔1080对应，然后将所述第二转轴107分别穿过所述第二轴套孔10460与所述第第四轴套孔1080，完成所述锁扣件108的安装。接着，将所述第二卡持件110的一端套在所述锁扣件108的第五轴套孔1082所在的一端上，并使得所述第五轴套孔1082与所述第六轴套孔1104对应，然后将所述第三转轴109分别穿过所述第五轴套孔1082与所述第六轴套孔1104，完成所述第二卡持件110的安装。安装完成后的图请参看图4及图5所示。
图4及图5所示的状态为所述卡锁机构103处于解锁状态的图。在所述解锁状态下，所述第一卡持件106的第一卡扣部1066与所述第二卡持件110的第二卡扣部1106未卡扣在一起。此时，可以便于将机臂放入所述夹持槽1041。当所述机臂置于所述夹持槽1041时，将所述第一卡持件106向所述第二卡持件110的方向旋转，所述第二卡持件110向所述第一卡持件106的方向旋转，同时所述锁扣件108朝向远离所述卡持座104的底板1040的方向旋转，从而使得所述第二卡持件110的第二卡扣部1106能够与所述第一卡持件106的第一卡扣部1066相卡合。然后向下按压所述锁扣件108使得所述锁扣件108朝向所述卡持座104的底板1040的方向旋转，当旋转到一指定位置，例如所述锁扣件108贴合在所述夹持壁1042的侧壁时，所述第二卡持件110受到向下的拉力而与所述第一卡持件106紧紧卡合在一起。所述第一卡持件106受到所述第二卡持件110横向的拉力，使得两夹持壁1042相向靠近从而紧紧固定所述机臂于所述夹持槽1041内。图6及图7分别为所述卡锁机构103处于锁固状态的图，其中机臂未插入其中。
所述螺旋桨保护罩10可用于无人机，所述无人机可用于任何适宜的环境，例如在空中（例如旋翼飞行器、固定翼飞行器或固定翼与旋翼混合的飞行器），在水中（例，船或潜艇），在地面上（例，摩托车，汽车，卡车，公交车，火车等），在太空中（例，航天飞机、卫星或探测器），或在地下（例如地铁），或上述环境的任意组合。在本实施例中，所述无人机为旋翼飞行器，其中所述旋翼可为单旋翼、双旋翼、三旋翼、四旋翼、六旋翼及八旋翼等。为便于描述，如下实施例中的无人机以四旋翼飞行器为例进行说明。
请参阅图8，图8示出了本发明实施例的包括有所述螺旋桨保护罩10的一无人机1。所述无人机1包括机身12、自所述机身12延伸的多个机臂14。每一机臂远离所述机身12的末端卡持在螺旋桨保护罩10的所述卡锁机构103的U形夹持槽1041内。所述螺旋桨保护罩10的安装座102用于装设动力机构16。所述机臂14的末端部上开设有动力机构安装部，所述动力机构安装部与所述安装座102对应。所述动力机构16可通过所述动力机构安装部及所述安装座102将所述机臂14及所述螺旋桨保护罩10连接在一起。例如，所述动力机构16可包括电机，所述电机安装在所述机臂的动力机构安装部上，所述电机的转轴连接螺旋桨。所述动力机构16可包括旋翼、螺旋桨、叶片、引擎、电机、轮组、轴、磁铁或喷嘴中的一个或多个。所述无人机1可包括一个、两个、三个、四个或多个动力机构。所述动力机构16可为相同的类型。可替代地，所述一个或多个动力机构可为不同类型的动力机构。在一些实施例中，所述动力机构16可使得所述无人机1垂直地从一表面起飞或垂直地着陆于一表面，而不需要所述无人机做任何的水平移动（例，不需要在跑道上滑行）。可选地，所述无人机1可用于操作以使得所述无人机1在指定的位置和方位上空悬停。
例如，所述无人机1可包括为无人机提供提升力及推力的多个水平导向的旋翼。所述多个水平导向的旋翼可被作动以提供垂直起飞、垂直着陆、悬停能力至所述无人机1。在一些实施例中，一个或多个水平导向的旋翼可顺时针旋转，同时一个或多个水平旋翼可逆时针旋转。例如，顺时针旋转的旋翼的数量可等于逆时针旋转的旋翼。每一水平导向旋翼的转速可独立地变化以控制所述旋翼产生的提升力及/或推力，从而调整所述无人机1的空间方位、速率，及/或加速度（例，相对于三维平移自由度和三维旋转自由度）。
虽然图中所示的实施例仅仅示出了四个机臂，可以理解的是，所述无人机1可以包括其他适宜数量的机臂，例如六个、八个等。
两个相邻的螺旋桨保护罩可以通过连接结构11相连接（如图1所示），连接在一起的螺旋桨保护罩具有更强的抗击能力。可以理解的是，在其他实施例中，两个螺旋桨保护罩10也可以一体成型为一个整体。在一些实施例中，位于所述机身12同侧的两个相邻螺旋桨保护罩10能够通过快拆自锁机构连接在一起，使用时便于安装在一起，收纳时便于拆开分离而收纳。在一些实施例中，位于所述机身12同侧的两个螺旋桨保护罩10也可以通过可折叠的连接装置连接在一起，当使用时能够展开至图8所示的状态，当需要收纳时，能够折叠而重合在一起以便于收纳。
当所述螺旋桨保护罩受到撞击时，包过所述机臂14的卡锁机构的卡扣及转轴等组件能够承受较大的撞击力（例如6米/S速度发生碰撞），从而保护螺旋桨不受到或者受到较小损坏，以及保护外物受到转动的螺旋桨造成的伤害。
可以理解的是，所述底板1040及所述夹持壁1042所围设的夹持槽1041的形状不限于U形，所述夹持槽1041的形状可根据机臂的形状进行适应性改变，例如若所需要夹持的机臂为椭圆形，所述夹持槽1041的形状即可为开口的椭圆形。
可以理解的是，所述第一卡持件106的第一卡扣部1066与所述第二卡持件110的第二卡扣部1106的固定方式不限于图所示的卡勾方式，可以为任意适宜的可分离的固定方式，例如卡槽与卡勾，锁扣与锁舌等。
可以理解的是，在图所示的实施例中，所述第一卡持件106中心设有第一通孔1062，为所述第一卡持件106受到撞击提供缓冲。在其他一些实施例中，所述第一通孔1062可以省略，所述第一卡持件106的本体为完整的一片。
可以理解的是，所述第一转轴105与所述第一卡持件106可一体成型或通过其他方式固定在一起；在其他一些实施例中，所述第一转轴105也可以与所述夹持壁1042一体成型或固定在一起，而所述第一卡持件106能够可分离地连接在所述第一转轴105上。
可以理解的是，所述第二转轴107与所述夹持壁1042可以一体成型或固定在一起，而所述锁扣件108能够分离地连接在所述第二转轴107上。在其他一些实施例中，所述第二转轴107也可以与所述锁扣件108一体成型或固定在一起。同理，所述第三转轴109也可以与所述锁扣件108一体成型或固定在一起。在其他一些实施例中，所述第三转轴109也可以与所述第二卡持件110一体成型或固定在一起，而所述锁扣件108能够分离地连接在所述第三转轴109上。
可以理解的是，所述安装座102可以省略，而所述动力机构无需承载在安装座上。
可以理解的是，所述锁扣件108可以省略，所述第二卡持件110可以直接转动连接在所述卡持座104上远离所述第一卡持件106的外侧壁上，所述第一卡持件106与所述第二卡持件110能够分离地固定在一起。
可以理解的是，所述锁扣件108及所述第二卡持件110均可省略，此时，所述第一卡持件106能够直接与所述卡持座106的夹持臂相扣合及分离。
另外，对于本领域的普通技术人员来说，可以根据本发明的技术构思做出其它各种相应的改变与变形，而所有这些改变与变形都应属于本发明权利要求的保护范围。

Claims (29)

  1. 一种螺旋桨保护罩，所述螺旋桨保护罩包括保护支架，其特征在于：所述螺旋桨保护罩还包括设置在所述保护支架上的卡锁机构，所述卡锁机构能够分离地安装于无人机的机臂上，所述卡锁机构环绕所述机臂以使所述卡锁机构能够套设在所述机臂上。
  2. 如权利要求1所述的螺旋桨保护罩，其特征在于：所述螺旋桨保护罩还包括用于安装动力机构的安装座，所述安装座设置在所述卡锁机构及所述保护支架之间。
  3. 如权利要求2所述的螺旋桨保护罩，其特征在于：所述安装座包括安装槽及开设在安装槽底部的通孔，所述安装槽用于承载动力装置；所述通孔用于供无人机的脚架穿设。
  4. 如权利要求2所述的螺旋桨保护罩，其特征在于：所述保护支架包括径向支架和连接所述径向支架的弧形支架。
  5. 如权利要求4所述的螺旋桨保护罩，其特征在于：所述安装座设置在所述弧形支架的圆心处。
  6. 如权利要求4所述的螺旋桨保护罩，其特征在于：所述弧形支架所在的圆与所述螺旋桨的叶片的旋转面所在的圆为同心圆，且所述弧形支架所在的圆的直径大于所述螺旋桨的叶片的旋转面所在的圆的直径。
  7. 如权利要求4所述的螺旋桨保护罩，其特征在于：所述保护支架的数量至少为两个，相邻的两保护支架的弧形支架能够脱卸地连接在一起。
  8. 如权利要求4所述的螺旋桨保护罩，其特征在于：收纳时，所述保护支架能够互相折叠重合。
  9. 如权利要求8所述的螺旋桨保护罩，其特征在于：所述弧形支架上设置连接结构，所述连接结构可对折以使所述弧形支架能够折叠重合。
  10. 如权利要求1所述的螺旋桨保护罩，其特征在于：所述卡锁机构位于无人机的与螺旋桨的电机之间。
  11. 如权利要求1所述的螺旋桨保护罩，其特征在于：所述卡锁机构包括卡持座，所述卡持座包括底板及自所述底板两相对侧延伸的夹持壁，所述底板及两所述夹持壁共同围设一夹持槽，所述机臂能够被夹持在所述夹持槽内。
  12. 如权利要求11所述的螺旋桨保护罩，其特征在于：所述夹持槽形状与所述机臂形状相适应。
  13. 如权利要求11所述的螺旋桨保护罩，其特征在于：所述夹持槽为U形或开口的椭圆形。
  14. 如权利要求11所述的螺旋桨保护罩，其特征在于：所述卡锁机构包括转动连接在其中一夹持壁背离所述夹持槽的外侧表面的第一卡持件及转动连接在另一夹持臂背离所述夹持槽的外侧表面的锁扣件，所述锁扣件的自由端转动连接一第二卡持件，所述第一卡持件与所述第二卡持件能够分离地固定在一起。
  15. 如权利要求14所述的螺旋桨保护罩，其特征在于：所述卡锁机构处于锁固状态时，所述锁扣件的自由端靠近所述卡持座的夹持壁，且所述第一卡持件与所述第二卡持件配合固定；所述卡锁机构处于解锁状态时，所述锁扣件的自由端远离所述卡持座的夹持壁，且所述第一卡持件与所述第二卡持件分离。
  16. 如权利要求14所述的螺旋桨保护罩，其特征在于：所述其中一夹持壁的外侧表面设置有第一轴套，所述另一夹持壁的外侧表面设置有第二轴套，所述第一轴套用于安装所述第一卡持件，所述第二轴套用于安装所述第二卡持件。
  17. 如权利要求16所述的螺旋桨保护罩，其特征在于：所述第一轴套数量为两个，平行间隔设置，第一卡持件一端设置有三个间隔设置的第三轴套，所述两第一轴套及所述三第三轴套能够相互交叉设置，以使得所述第一轴套及所述第三轴套同轴。
  18. 如权利要求17所述的螺旋桨保护罩，其特征在于：所述第三轴套的数量为两个，所述第一轴套能够架设在两所述第三轴套之间。
  19. 如权利要求16所述的螺旋桨保护罩，其特征在于：所述第一卡持件中间设置有通孔。
  20. 如权利要求16所述的螺旋桨保护罩，其特征在于：所述第一轴套沿着其所在的夹持壁朝向所述底板的方向延伸形成一加强肋。
  21. 如权利要求16所述的螺旋桨保护罩，其特征在于：所述第二轴套数量为两个，平行间隔设置，所述锁扣件一端设置有第四轴套，所述第四轴套能够夹设在两个所述第二轴套之间，以使得所述第二轴套及所述第四轴套同轴。
  22. 如权利要求16所述的螺旋桨保护罩，其特征在于：所述锁扣件另一端设置有第五轴套，所述第二卡持件能够转动连接在所述第五轴套上。
  23. 如权利要求22所述的螺旋桨保护罩，其特征在于：所述第二卡持件一端设置有第六轴套，所述第二卡持件转动连接在所述锁扣件上时，所述第五轴套与所述第六轴套同轴。
  24. 如权利要求16所述的螺旋桨保护罩，其特征在于：所述第二卡持件中间形成有通孔，所述锁扣件及所述第二轴套能够容设在所述通孔内。
  25. 如权利要求11所述的螺旋桨保护罩，其特征在于：所述卡锁机构包括转动连接在其中一夹持壁背离所述夹持槽的外侧表面的第一卡持件，所述第一卡持件能够分离地与另一夹持壁扣合固定。
  26. 如权利要求11所述的螺旋桨保护罩，其特征在于：所述卡锁机构包括转动连接在其中一夹持壁背离所述夹持槽的外侧表面的第一卡持件，及转动连接在另一夹持壁背离所述夹持槽的外侧表面的第二卡持件，所述第一卡持件与所述第二卡持件能够分离地扣合固定。
  27. 一种无人机，包括机身、与所述机身连接的多个机臂及多个螺旋桨组件，其特征在于：所述无人机还包括权利要求1到权利要求26任一项所述的螺旋桨保护罩，所述卡锁机构设置在所述机臂上并位于所述和所述螺旋桨组件之间。
  28. 如权利要求27所述的无人机，其特征在于：所述螺旋桨组件包括电机和与所述电机连接的螺旋桨，所述电机能够承载于所述螺旋桨保护罩上，所述螺旋桨位于所述螺旋桨保护罩的轮廓以内。
  29. 如权利要求27所述的无人机，其特征在于：位于所述机身同侧的相邻机臂上连接的螺旋桨保护罩能够连接在一起。
PCT/CN2016/100433 2016-09-27 2016-09-27 螺旋桨保护罩及使用该螺旋桨保护罩的无人机 WO2018058328A1 (zh)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110972474A (zh) * 2018-11-30 2020-04-07 深圳市大疆创新科技有限公司 保护壳、电机组件、机臂组件及无人机

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108058818A (zh) * 2017-12-26 2018-05-22 昆山优尼电能运动科技有限公司 无人机桨保护架
CN109466758B (zh) * 2018-06-21 2020-03-24 国网浙江江山市供电有限公司 具有球型防摔护架的无人机装置
CN210592415U (zh) * 2019-07-22 2020-05-22 深圳市道通智能航空技术有限公司 螺旋桨保护罩及飞行器
CN112638774A (zh) * 2020-03-24 2021-04-09 深圳市大疆创新科技有限公司 螺旋桨的保护罩和无人机
CN212766735U (zh) * 2020-04-27 2021-03-23 深圳市大疆创新科技有限公司 旋翼保护机构及飞行器
CN112027076B (zh) * 2020-08-24 2022-03-22 王呼呼 一种能够对机翼进行保护的无人机转运装置

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN204822076U (zh) * 2015-07-27 2015-12-02 致导科技（北京）有限公司 一种无人机旋翼保护架及无人机
CN205131658U (zh) * 2015-09-01 2016-04-06 湖南云顶智能科技有限公司 用于无人机的螺旋桨保护装置
CN205150236U (zh) * 2015-11-20 2016-04-13 零度智控（北京）智能科技有限公司 螺旋桨顶部保护装置
CN205150240U (zh) * 2015-11-20 2016-04-13 零度智控（北京）智能科技有限公司 螺旋桨底部保护装置
CN205524937U (zh) * 2016-01-29 2016-08-31 深圳市大疆创新科技有限公司 螺旋桨保护罩及使用该螺旋桨保护罩的机臂结构、无人机

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN203996889U (zh) * 2014-07-04 2014-12-10 深圳市嘉兰图设计有限公司 四轴飞行器螺旋桨保护罩系统
CN104986331B (zh) * 2015-07-27 2017-12-12 致导科技（北京）有限公司 一种无人机旋翼保护架及无人机
CN205098485U (zh) * 2015-11-06 2016-03-23 刘东昌 一种可折叠模块化无人机保护结构

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN204822076U (zh) * 2015-07-27 2015-12-02 致导科技（北京）有限公司 一种无人机旋翼保护架及无人机
CN205131658U (zh) * 2015-09-01 2016-04-06 湖南云顶智能科技有限公司 用于无人机的螺旋桨保护装置
CN205150236U (zh) * 2015-11-20 2016-04-13 零度智控（北京）智能科技有限公司 螺旋桨顶部保护装置
CN205150240U (zh) * 2015-11-20 2016-04-13 零度智控（北京）智能科技有限公司 螺旋桨底部保护装置
CN205524937U (zh) * 2016-01-29 2016-08-31 深圳市大疆创新科技有限公司 螺旋桨保护罩及使用该螺旋桨保护罩的机臂结构、无人机

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110972474A (zh) * 2018-11-30 2020-04-07 深圳市大疆创新科技有限公司 保护壳、电机组件、机臂组件及无人机

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