WO2018209765A1 - 无人飞行器的桨叶保护装置及无人机系统 - Google Patents

无人飞行器的桨叶保护装置及无人机系统 Download PDF

Info

Publication number
WO2018209765A1
WO2018209765A1 PCT/CN2017/090415 CN2017090415W WO2018209765A1 WO 2018209765 A1 WO2018209765 A1 WO 2018209765A1 CN 2017090415 W CN2017090415 W CN 2017090415W WO 2018209765 A1 WO2018209765 A1 WO 2018209765A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
guard assembly
assembly
blade guard
protection device
Prior art date
Application number
PCT/CN2017/090415
Other languages
English (en)
French (fr)
Inventor
张蕾
唐尹
金时润
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 CN201780068011.5A priority Critical patent/CN109906185A/zh
Publication of WO2018209765A1 publication Critical patent/WO2018209765A1/zh

Links

Images

Classifications

    • 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
    • B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/40—Engine management systems

Definitions

  • the invention relates to the technical field of drones, in particular to a blade protection device and a drone system of an unmanned aerial vehicle.
  • UAVs are unmanned aircraft operated by radio remote control equipment and self-contained program control devices. They are widely used in aerial photography, agriculture, disaster relief, surveillance of infectious diseases, mapping, news reporting, film and television shooting and other fields. With the society's emphasis on the safety of drones, the actual demand for paddle guards has become stronger and stronger, and the impact resistance of existing paddle guards is not high, which affects the safety of unmanned aerial vehicles.
  • the technical problem to be solved by the present invention is to provide a blade protection device and an unmanned aerial vehicle system for an unmanned aerial vehicle, which have high impact resistance.
  • the present invention adopts a technical solution to provide a blade protection device for an unmanned aerial vehicle, the blade protection device including a first blade protection cover assembly, a second blade protection cover assembly and a buckle An assembly, wherein the first blade guard assembly and the second blade guard assembly are disposed on opposite sides of the UAV and are respectively engaged with the arm of the UAV, the lock assembly for locking the first blade
  • the boot assembly and the second blade guard assembly maintain the engaged state of the first blade guard assembly and the second blade guard assembly with the UAV.
  • the latch assembly includes a first latch body and a second latch body, the first latch body and the second latch body for detaching the first blade guard assembly and the second blade guard assembly The way to lock the connection.
  • first latch body is fixedly disposed on the first blade guard assembly
  • second latch The body is pivotally coupled to the second blade guard assembly and is pivotable relative to the second blade guard assembly for engagement with the first striker body
  • the second latch body comprises a pivot and a connecting plate, and the pivot is fixedly disposed on the second blade guard assembly.
  • the connecting plate and the pivot are detachably connected.
  • first blade guard assembly and the second blade guard assembly have a central symmetrical structure.
  • the first latch body is a post that is disposed in parallel with the pivot direction of the second latch body, and the second latch body is provided with a card slot corresponding to the post.
  • the first latch body is a buckle disposed in parallel with the pivot direction of the second latch body, and the second latch body is provided with a card slot corresponding to the buckle.
  • the first latch body is a first buckle disposed in parallel with the pivot direction of the second latch body, and the second latch body is provided with a second buckle corresponding to the first buckle.
  • the first blade guard assembly includes two first extending arms spaced apart from each other, the first latch body being fixedly disposed between the two first extending arms;
  • the second blade guard assembly includes two second extension arms spaced apart from one another, the second striker body being pivotally coupled between the two second extension arms.
  • the ends of the first extension arm and the second extension arm are provided with an alignment insertion structure to align the first blade protection cover assembly and the second blade protection cover assembly.
  • the first connecting member is further disposed between the two first extending arms, and the second connecting member is further disposed between the two second extending arms.
  • first blade guard assembly further includes a first lower card, the first lower card being engaged with a lower surface of one side of the unmanned aerial vehicle;
  • the second blade guard assembly further includes a second lower deck that engages a lower surface of the other side fuselage of the UAV.
  • the first blade protection cover assembly further comprises a first upper clamping plate and a first lower clamping plate, the first upper clamping plate and the first lower clamping plate are disposed at the first blade protection cover assembly and the second
  • the first blade protection cover assembly is respectively engaged with the two sides of the UAV, respectively, the upper blade and the lower surface of the two adjacent arms of the UAV are respectively engaged
  • the second blade protection cover assembly further includes an interval The second upper card and the second lower card, the second upper card and the second lower card
  • the first blade guard assembly and the second blade guard assembly are respectively engaged with the sides of the UAV, respectively, they are respectively clamped on the upper surface and the lower surface of the other two adjacent arms of the UAV.
  • the first blade guard assembly further includes two first side cards connected to the first upper card and the first lower card, and the two first side cards are respectively clamped to two adjacent arms On the adjacent side surface
  • the second blade guard assembly further includes two second side cards connected to the second upper card and the second lower card, and the two second side cards are clamped to the other two Adjacent side surfaces of adjacent arms.
  • the first protective cover assembly includes at least two first protective covers, at least two first protective covers are fixedly connected or separately disposed on the first extending arm, and the second protective cover assembly includes at least two second protective covers, at least two The second protective cover is fixedly connected or separately disposed on the second extending arm.
  • first protective cover and the second protective cover are fan-shaped covers.
  • another technical solution adopted by the present invention is to provide an unmanned aerial vehicle system including the blade protection device of any of the foregoing and the unmanned aerial vehicle, and the blade protection device is locked. On the fuselage of the unmanned aerial vehicle.
  • the invention has the beneficial effects that the present invention provides a blade protection device for an unmanned aerial vehicle and a drone system, the blade protection device comprising a first blade protection cover assembly and a second a pad guard assembly and a latch assembly, wherein the first blade guard assembly and the second blade guard assembly are disposed on opposite sides of the UAV and are respectively engaged with the sides of the UAV, the buckle The assembly is for locking the first blade guard assembly and the second blade guard assembly to maintain the engaged state of the first blade guard assembly and the second blade guard assembly with the unmanned aerial vehicle. Therefore, the present invention is engaged with the opposite sides of the UAV by the first blade guard assembly and the second blade guard assembly, respectively, so that the sides of the UAV can cancel part of the impact when encountering a collision object. The force, thereby enhancing the stability of the boot assembly, thereby improving the impact resistance of the blade guard assembly.
  • FIG. 1 is a schematic top view showing an exploded structure of an unmanned aerial vehicle system according to an embodiment of the present invention
  • FIG. 2 is a schematic top view showing the assembly of an unmanned aerial vehicle system according to an embodiment of the present invention
  • FIG. 3 is a side view showing a schematic structure of an unmanned aerial vehicle system according to an embodiment of the present invention.
  • FIG. 4 is a schematic structural view of a lock assembly of an unmanned aerial vehicle according to an embodiment of the present invention.
  • FIG. 5 is a schematic structural diagram of another lock assembly of an unmanned aerial vehicle according to an embodiment of the present invention.
  • the UAV system 10 of the present embodiment includes an unmanned aerial vehicle 100 and a blade protection device 200.
  • the unmanned aerial vehicle 100 includes a fuselage 180, arms 101-104, blades 106, and a motor 190 that drives the blades 106.
  • the arms 101 and 102 are disposed at both ends of one side of the body 180 along the long axis direction of the body 180, and the arms 103 and 104 are disposed on the other side of the body 180 along the long axis direction of the body 180. Both ends.
  • Two blades 106 are disposed on each of the motors 190.
  • the blade guard 200 is shielded from the periphery of the blade 106 protecting the unmanned aerial vehicle 100 for protecting the blade 106 from impact or the like.
  • the blade protection device 200 includes a first blade guard assembly 11 , a second blade guard assembly 12 , and a latch assembly 13 .
  • the first blade guard assembly 11 and the second blade guard assembly 12 are disposed on opposite sides 150 and 160 of the UAV 100 and are respectively engaged with the two sides of the UAV 100, and the latch assembly 13 is used for The first blade guard assembly 11 and the second blade guard assembly 12 are locked to maintain the engaged state of the first blade guard assembly 11 and the second bucket guard assembly 12 with the unmanned aerial vehicle 100.
  • the first blade protection cover assembly 11 and the second blade protection cover assembly 12 are disposed at the position of the unmanned aerial vehicle 100 at opposite sides along the long axis direction of the body 180 of the unmanned aerial vehicle 100. That is, 150 and 160 shown in FIG.
  • first blade guard assembly 11 and the second blade guard assembly 12 are disposed at the position of the unmanned aerial vehicle 100 and may also be opposite to each other along the short axis direction of the fuselage 180 of the unmanned aerial vehicle 100. side.
  • first blade guard assembly 11 and the second blade guard assembly 12 are The structure is completely symmetrical, so that only one mold opening is required in the process, and two blade guard assemblies can be made, which simplifies the manufacturing process. In addition, the center of gravity movement of the UAV 100 can be minimized by the blade guard assembly.
  • the first blade guard assembly 11 and the second blade guard assembly 12 are respectively disposed on opposite sides of the unmanned aerial vehicle 100, and respectively engaged with the two sides of the unmanned aerial vehicle 100, When the first paddle guard assembly 11 and/or the second paddle guard assembly 12 receives an impact, the unmanned aerial vehicle 100 can offset a portion of the impact force, thereby enhancing the first blade guard assembly 11 and the second blade.
  • the stability of the boot assembly 12 enhances the impact resistance of the first blade guard assembly 11 and the second blade guard assembly 12.
  • the locking component 13 can be locked in a non-removable locking manner, that is, the first blade guard assembly 11 and the second blade guard assembly 12 are non-detachably locked.
  • Non-removable locking connections may include hemmed connections, rivet connections, bonded connections, and welded connections.
  • the present invention does not limit the specific structure of the latch assembly 13, as long as the above-described non-detachable locking connection function is achieved.
  • the non-removable locking connection enhances the stability of the blade guard 100.
  • the assembly 13 is configured to releasably connect the first blade guard assembly 11 and the second blade guard assembly 12 in a detachable manner.
  • the latch assembly 13 includes a first latch body 131 and a second latch body 132. The first latch body 131 and the second latch body 132 are for detachably locking the first blade guard assembly 11 and the second blade guard assembly 12.
  • the first latch body 131 is fixedly disposed on the first blade guard assembly 11 .
  • the second latch body 132 is pivotally coupled to the second blade guard assembly 12 and is pivotable relative to the second blade guard assembly 12 to be engaged with the first latch body 131. More specifically, the first latch body 131 can be a post 133 disposed in parallel with the pivotal direction of the second latch body 132.
  • the second latch body 132 includes a pivot 1321 and a connecting plate 1322.
  • the pivot 1321 is fixedly disposed.
  • the connecting plate 1322 and the pivot 1321 are detachably connected.
  • the second latch body 132 is provided with a card slot 134 corresponding to the post 133.
  • a card slot 134 corresponding to the post 133 is disposed on the connecting plate 1322. Therefore, the latch assembly 13 of the present embodiment can realize the detachable connection through the card slot 134 and the post 133, has a simple structure, and is light in weight, and is suitable for a small-sized unmanned aerial vehicle.
  • the first latch body 131 can be disposed as a buckle 136 disposed parallel to the pivotal direction of the second latch body 132 , and the second latch body 132 is provided with a buckle 136 corresponds to the card slot 137.
  • the buckle 136 includes a hook-shaped fastening portion 138. During the engaging process, the card slot 137 is pivoted to engage the buckle 136 into the slot 137, and the slot 137 is engaged by the hook-shaped engaging portion 138 of the buckle 136.
  • the first latch body 131 can be disposed as a first buckle 141 disposed parallel to the pivotal direction of the second latch body 132 , and the second latch body 132 is disposed with the first buckle 141 .
  • the first buckle 141 includes a hook-shaped first fastening portion 143
  • the second buckle 142 includes a hook-shaped second fastening portion 144.
  • the second buckle 142 is pivoted in the direction of the first buckle 141 and is engaged with each other by the first fastening portion 143 and the second fastening portion 144.
  • the second latch body 132 is further provided with a reinforcing structure 135.
  • the reinforcing structures 135 may be protrusions that are arranged to cross each other for reinforcing the strength of the second latch body 132.
  • first blade guard assembly 11 includes two first extension arms 111 and 112 spaced apart from each other, and the first lock body 131 is fixedly disposed between the two first extension arms 111 and 112.
  • the second blade guard assembly 12 further includes two second extension arms 121 and 122 spaced apart from each other, the second lock body 132 being pivotally coupled between the two second extension arms 121 and 122.
  • the post of the first latch body 131 is fixedly disposed between the two first extending arms 111 and 112, and the pivot 1321 of the second latch body 132 is pivotally connected to the two second extending arms 121 and 122. between.
  • first extension arms 111 and 112 extend from the first blade protection cover assembly 11 toward the second blade protection cover assembly 12, and the second extension arms 121 and 122 extend from the second blade protection cover assembly 12 to the first The direction of the pad guard assembly 11 extends.
  • first extension arms 111 and 112 can also be aligned with the second extension arms 121 and 122, specifically, the ends of the first extension arms 111 and 112 and the second extension arms 121 and The ends of the 122 are respectively provided with alignment plug structures 113 and 123 to enable the first blade guard assembly 11 and the second blade guard assembly 12 to achieve the alignment.
  • the ends of the first extension arms 111 and 112 are away from the end of the first blade protection cover assembly 11, and similarly, the ends of the second extension arms 121 and 122 are away from the end of the second blade protection cover 12. unit.
  • the end of one of the two first extension arms 111 and 112 is provided with a post 114, and the end of the other of the two first extension arms 111 and 112 is provided with a socket 115.
  • the end of the first extension arm 111 is provided with a post 114, and the end of the first extension arm 112 is provided with a socket 115.
  • An end of one of the two second extension arms 121 and 122 is provided with a socket that is mated with the insertion post 114, and an end of the other of the two second extension arms 121 and 122 is provided with the insertion hole 115 As shown in FIG.
  • the end of the second extension arm 121 is provided with a socket (not shown) that is mated with the insertion post 114 , and the end of the second extension arm 122 is disposed.
  • a post 124 that is mated with the jack 115.
  • the size of the plugs 114 and 124 and the size of the jacks on the jack 115 and the extension arm 121 can be the same, so that the same set of templates can be formed during the manufacturing process, thereby achieving cost saving.
  • a post may be respectively disposed at the ends of the two first extension arms 111 and 112, and the insertion holes corresponding to the post are respectively disposed at the ends of the two second extension arms 121 and 122.
  • a socket is respectively provided at the ends of the two first extension arms 111 and 112, and a post corresponding to the insertion hole is respectively disposed at the ends of the two second extension arms 121 and 122.
  • first connecting member 1112 is further disposed between the two first extending arms 111 and 112
  • second connecting member 1212 is further disposed between the two second extending arms 121 and 122.
  • the first connecting member 1112 is disposed closer to the post 114 and the insertion hole 115 with respect to the post 133.
  • the second connector 1212 is disposed closer to the post 124 and the second receptacle relative to the pivot 1321.
  • the first connector 1112 and the second connector 1212 are used to reinforce the strength of the first extension arms 111 and 112 and the second extension arms 121 and 122, respectively.
  • first blade guard assembly 11 further includes a first upper card plate 116 and a first lower card plate 117 which are spaced apart.
  • the first upper deck 116 and the first lower deck 117 are disposed to be respectively held when the first blade guard assembly 11 and the second blade guard assembly 12 are respectively engaged with the sides of the unmanned aerial vehicle 100.
  • Upper and lower arms 101 and 102 of the human aircraft 100 On the surface and on the lower surface.
  • the two adjacent arms of the UAV 100 that the first upper card 116 and the first lower card 117 are engaged may be disposed along the long axis direction of the body 180 of the UAV 100 and Two adjacent arms on the same side of the fuselage 180, namely the arms 101 and 102 shown in FIG.
  • the two adjacent arms of the UAV 100 that the first upper card board 116 and the first lower card board 117 are held may also be disposed along the short axis direction of the body 180 of the UAV 100. And two adjacent arms that are located on the same side of the fuselage 180. That is, the arms 101 and 104 or the arms 102 and 103 shown in FIG.
  • the second blade guard assembly 12 further includes a second upper card plate 125 and a second lower card plate 126 spaced apart, the second upper card plate 125 and the second lower card plate 126 being in the first blade guard assembly 11 and
  • the second blade guard assembly 12 is configured to be respectively retained by the unmanned aerial vehicle 100 when the first blade guard assembly 11 and the second blade guard assembly 12 are respectively engaged with the sides of the unmanned aerial vehicle 100 Upper and lower surfaces of two adjacent arms 103 and 104.
  • the two adjacent arms of the UAV 100 that the second upper card 125 and the second lower card 126 are engaged may be along the long axis of the body 180 of the UAV 100.
  • the two adjacent arms of the UAV 100 that the second upper card plate 125 and the second lower card plate 126 are engaged may also be disposed along the short axis direction of the body 180 of the UAV 100. And two adjacent arms that are located on the same side of the fuselage 180. That is, the arms 101 and 104 or the arms 102 and 103 shown in FIG.
  • first blade guard assembly 11 further includes two first side cards 118 and 119 connected to the first upper card 116 and the first lower card 117, and the two first side cards 118 and 119.
  • the second blade guard assembly 12 further includes two second side cards 127 and 128 coupled to the second upper card 125 and the second lower card 126, the two second side cards 127 and 128 being used in The first blade guard assembly 11 and the second blade guard assembly 12 are respectively When the two sides of the UAV 100 are engaged, they are respectively held on the adjacent side surfaces of the other two adjacent arms 103 and 104.
  • the side cards described above are all inclined, and the angle of the inclination corresponds to the inclination angle of the arm that is held. Therefore, when the side card is engaged with the arm, the surface to be held can be attached without a gap, thereby obtaining a better clamping and fixing function.
  • first blade guard assembly 11 further includes at least two first protective covers, and at least two first protective covers are fixedly connected or separately disposed to the first extending arms 111 and 112.
  • the second boot assembly 12 includes at least two second protective covers, and at least two second protective covers are fixedly coupled or separately disposed to the second extending arms 121 and 122.
  • each protective cover assembly is provided with only two protective covers, that is, two first protective covers 110 and 120 and two second protective covers 130 and 140.
  • each blade is correspondingly provided with a protective cover.
  • the specific settings are as follows.
  • two or more protective covers may also be provided for each blade.
  • the two first protective covers 110 and 120 are disposed on the first upper card plate 116 and further covered on the periphery of the blades 105 and 106 disposed on the two adjacent arms 101 and 102.
  • Two first extension arms 111 and 112 are respectively disposed on the two first protective covers 110 and 120.
  • first blade guard assembly 11 further includes first connecting arms 1101 and 1201 extending downward from the first protective covers 110 and 120, respectively, and the first connecting arm 1101 is configured to connect the first protective cover 110 and the first
  • the upper connecting plate 1201 is configured to connect the first protective cover 120 and the first upper clamping plate 116.
  • the first protective covers 110 and 120 are disposed on the first upper card board 116.
  • Two second protective covers 130 and 140 are disposed on the second upper clamping plate 125 and further cover the periphery of the blades 107 and 108 disposed on the other two adjacent arms 103 and 104, and the two second extending arms 121 and 122 are respectively disposed on the two second protective covers 130 and 140.
  • the second blade guard assembly 12 further includes second connecting arms 1301 and 1401 extending downward from the second protective covers 130 and 140, respectively, and the second connecting arm 1301 is for connecting the second protective cover 130 and the second
  • the upper clamping plate 125 is connected to the second protective cover 140 And a second upper card plate 125.
  • the second protective covers 130 and 140 are disposed on the second upper card plate 125.
  • first lower card 117 and the second lower card 126 may be disposed.
  • the first lower card 117 is engaged on the lower surface of one side of the body, and the second lower card 126 is engaged.
  • the first lower card board 117 is respectively connected to the first protective covers 110 and 120 through the first connecting arms 1101 and 1201
  • the second lower clamping board 12 is respectively connected to the second protective cover 130 through the second connecting arms 1301 and 1401. Connected to 140.
  • the first lower card plate 117 and the second lower card plate 126 may be disposed along the long axis direction of the body, or may be disposed along the short axis direction of the body.
  • two first lower card plates 117 and two second lower card plates 126 may be disposed in parallel, which may be They are spaced apart along the long axis of the fuselage and are engaged on both sides of the fuselage along the long axis direction, thereby enhancing card cooperation.
  • the first protective covers 110 and 120 of the present embodiment are two adjacent protective covers disposed along the long axis direction of the body 180 of the unmanned aerial vehicle 100 and located on the same side of the body 180.
  • the second protective covers 130 and 140 are also two adjacent protective covers disposed along the long axis of the fuselage 180 of the unmanned aerial vehicle 100 and located on the same side of the fuselage 180.
  • the first protective covers 110 and 120 and the second protective covers 130 and 140 are respectively disposed on two opposite sides of the unmanned aerial vehicle 100.
  • the first extension arms 111 and 112 extend from the first protection covers 110 and 120 to the second protection covers 130 and 140, respectively, and the second extension arms 121 and 122 respectively extend from the second protection covers 130 and 140, respectively.
  • the directions of the first protective covers 110 and 120 extend.
  • the posts 133 disposed between the two first extension arms 111 and 112 and The card slot 134 of the second latch body 132 disposed between the two second extension arms 121 and 122 can be snap-fitted in the middle of the body 180 of the UAV 100, thereby increasing the fixing strength.
  • the two first protective covers 110 and 120 are fixedly connected to the first extending arms 111 and 112, and the two second protective covers 130 and 140 are fixedly connected to the second extending arms 121 and 122.
  • the two first protective covers 110 and 120 and the two second protective covers 130 and 140 can be made by integral molding.
  • the first protective cover 110 can also be A detachable member is disposed between the and the 120 and the second protective covers 130 and 140, and the first protective covers 110 and 120 and the second protective covers 130 and 140 are detachably connected.
  • a hinge structure is provided between the first protective covers 110 and 120 and the second protective covers 130 and 140 such that the first protective covers 110 and 120 are connected in an articulated manner.
  • first protective covers 110 and 120 and the second protective covers 130 and 140 may not be connected to each other. That is, the first protective covers 110 and 120 are separately disposed on the first extending arms 111 and 112, and the second protective covers 130 and 140 are separately disposed on the second extending arms 121 and 122.
  • the first protective covers 110 and 120 and the second protective covers 130 and 140 are both fan-shaped covers, and the inside of the sector cover is provided with a support arm 170 for reinforcing the strength of the sector cover.
  • the number of support arms 170 can be set as desired.
  • the support arm 170 enhances the strength of the boot on the one hand and the UAV 100 when the UAV 100 hits an obstacle on the other hand.
  • the fan-shaped cover body can be set at 270 degrees, which is advantageous for lightening the unmanned aerial vehicle, and can also prevent the protective cover from blocking the camera or other visual sensor disposed on the unmanned aerial vehicle.
  • the angle of the scallop can also be set to other as long as it does not interfere with the normal operation of the camera and other vision sensors.
  • the first protective covers 110 and 120 and the second protective covers 130 and 140 may be provided in a circular cover structure.
  • the present invention can quickly disassemble the blade guard assembly, facilitate replacement, and save time.
  • the stability of the blade guard assembly is enhanced, thereby improving the impact resistance of the blade guard assembly.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

一种无人飞行器(100)的桨叶保护装置(200)及无人机系统(10)。桨叶保护装置(200)包括第一桨叶保护罩组件(11)、第二桨叶保护罩组件(12)以及锁扣组件(13)，其中第一桨叶保护罩组件(11)和第二桨叶保护罩组件(12)设置于无人飞行器(100)的相对两侧(150,160)，且分别与无人飞行器(100)的机臂(101,102,103,104)卡合，锁扣组件(13)用于锁定第一桨叶保护罩组件(11)与第二桨叶保护罩组件(12)，以保持第一桨叶保护罩组件(11)及第二桨叶保护罩组件(12)与无人飞行器(100)的卡合状态。本桨叶保护装置(200)和无人机系统(10)增强了桨叶保护罩组件(11,12)的稳定性，从而提高了桨叶保护罩组件(11,12)的抗冲击性能。

Description

无人飞行器的桨叶保护装置及无人机系统 技术领域
本发明涉及无人机技术领域，尤其是涉及一种无人飞行器的桨叶保护装置及无人机系统。
背景技术
无人机是利用无线电遥控设备和自备的程序控制装置操纵的不载人飞机，其在航拍、农业、灾难救援、监控传染病、测绘、新闻报道、影视拍摄等领域方面得到广泛的应用。随着社会对无人机安全性的重视，对桨保护罩的实际需求变得越来越强，现有的桨保护罩的抗冲击性能不高，影响无人飞行器的安全。
发明内容
本发明主要解决的技术问题是提供一种无人飞行器的桨叶保护装置及无人机系统，具有较高的抗冲击性能。
为解决上述技术问题，本发明采用的一个技术方案是：提供一种无人飞行器的桨叶保护装置，桨叶保护装置包括第一桨叶保护罩组件、第二桨叶保护罩组件以及锁扣组件，其中第一桨叶保护罩组件和第二桨叶保护罩组件设置于无人飞行器的相对两侧，且分别与无人飞行器的机臂卡合，锁扣组件用于锁定第一桨叶保护罩组件与第二桨叶保护罩组件，以保持第一桨叶保护罩组件及第二桨叶保护罩组件与无人飞行器的卡合状态。
其中，锁扣组件包括第一锁扣主体和第二锁扣主体，第一锁扣主体和第二锁扣主体用于将第一桨叶保护罩组件和第二桨叶保护罩组件以可拆卸方式锁定连接。
其中，第一锁扣主体固定设置于第一桨叶保护罩组件上，第二锁扣 主体枢轴连接于第二桨叶保护罩组件上，并能够相对于第二桨叶保护罩组件枢轴转动成与第一锁扣主体卡合固定。
其中，第二锁扣主体包括枢轴和连接板，枢轴固定设置于第二桨叶保护罩组件上。
其中，连接板和枢轴可拆卸连接。
其中，第一桨叶保护罩组件和第二桨叶保护罩组件呈中心对称结构。
其中，第一锁扣主体为与第二锁扣主体的枢轴方向平行设置的卡柱，第二锁扣主体上设置有与卡柱对应的卡槽。
其中，第一锁扣主体为与第二锁扣主体的枢轴方向平行设置的卡扣，第二锁扣主体上设置有与卡扣对应的卡槽。
其中，第一锁扣主体为与第二锁扣主体的枢轴方向平行设置的第一卡扣，第二锁扣主体上设置有与第一卡扣对应的第二卡扣。
其中，第一桨叶保护罩组件包括彼此间隔设置的两个第一延伸臂，第一锁扣主体固定设置于两个第一延伸臂之间；
第二桨叶保护罩组件包括彼此间隔设置的两个第二延伸臂，第二锁扣主体枢轴连接于两个第二延伸臂之间。
其中，第一延伸臂和第二延伸臂的端部设置有对位接插结构，以使第一桨叶保护罩组件和第二桨叶保护罩组件对位接插。
其中，两个第一延伸臂之间进一步设置有第一连接件，两个第二延伸臂之间进一步设置有第二连接件。
其中，第一桨叶保护罩组件进一步包括第一下卡板，第一下卡板卡合在无人飞行器的一侧机身的下表面；
第二桨叶保护罩组件进一步包括第二下卡板，第二下卡板卡合在无人飞行器的另一侧机身的下表面上。
其中，第一桨叶保护罩组件进一步包括间隔设置的第一上卡板和第一下卡板，第一上卡板和第一下卡板设置成在第一桨叶保护罩组件和第二桨叶保护罩组件分别与无人飞行器的两侧卡合时分别卡持于无人飞行器的两个相邻机臂的上表面和下表面上，第二桨叶保护罩组件进一步包括间隔设置的第二上卡板和第二下卡板，第二上卡板和第二下卡板用 于在第一桨叶保护罩组件和第二桨叶保护罩组件分别与无人飞行器的两侧卡合时分别卡持于无人飞行器的另外两个相邻机臂的上表面和下表面上。
其中，第一桨叶保护罩组件进一步包括连接于第一上卡板和第一下卡板的两个第一侧卡板，两个第一侧卡板分别卡持于两个相邻机臂的相邻侧表面上，第二桨叶保护罩组件进一步包括连接于第二上卡板和第二下卡板的两个第二侧卡板，两个第二侧卡板卡持于另外两个相邻机臂的相邻侧表面上。
其中，第一保护罩组件包括至少两个第一保护罩，至少两个第一保护罩固定连接或分开设置于第一延伸臂，第二保护罩组件包括至少两个第二保护罩，至少两个第二保护罩固定连接或分开设置于第二延伸臂。
其中，第一保护罩和第二保护罩为扇形罩体。
为解决上述技术问题，本发明采用的另一个技术方案是：提供一种无人机系统，该无人机系统包括前文任意一项的桨叶保护装置以及无人飞行器，桨叶保护装置锁扣于无人飞行器的机身上。
本发明的有益效果是：区别于现有技术的情况，本发明提供一种无人飞行器的桨叶保护装置及无人机系统，该桨叶保护装置包括第一桨叶保护罩组件、第二桨叶保护罩组件以及锁扣组件，其中第一桨叶保护罩组件和第二桨叶保护罩组件设置于无人飞行器的相对两侧，且分别与无人飞行器的两侧卡合，锁扣组件用于锁定第一桨叶保护罩组件与第二桨叶保护罩组件，以保持第一桨叶保护罩组件及第二桨叶保护罩组件与无人飞行器的卡合状态。因此，本发明通过第一桨叶保护罩组件和第二桨叶保护罩组件分别与无人飞行器的相对两侧卡合，使得在遇到碰撞物时，无人飞行器的两侧可以抵消部分撞击力，由此增强了保护罩组件的稳定性，从而提高了桨叶保护罩组件的抗冲击性能。
附图说明
图1是本发明实施例提供的一种无人机系统的爆炸俯视结构示意图；
图2是本发明实施例提供的一种无人机系统的组装俯视结构示意图；
图3是本发明实施例提供的一种无人机系统的侧视结构示意图；
图4是本发明实施例提供的一种无人飞行器的锁扣组件的结构示意图；
图5是本发明实施例提供的另一种无人飞行器的锁扣组件的结构示意图。
具体实施方式
请一并参阅图1-图3。本实施例的无人机系统10包括无人飞行器100和桨叶保护装置200。其中，无人飞行器100包括机身180、机臂101-104、桨叶106以及驱动桨叶106的电机190。其中，机臂101和102沿机身180的长轴方向设置在机身180的一侧的两端，机臂103和104沿机身180的长轴方向设置在机身180的另一侧的两端。电机190为四个，分别设置在机臂101-104的远离机身180的一端。每个电机190上设置两片桨叶106。
桨叶保护装置200罩设在保护无人飞行器100的桨叶106的外围，用于保护桨叶106免受撞击等。
其中，桨叶保护装置200包括第一桨叶保护罩组件11、第二桨叶保护罩组件12以及锁扣组件13。第一桨叶保护罩组件11和第二桨叶保护罩组件12设置于无人飞行器100的相对两侧150和160，且分别与无人飞行器100的两侧卡合，锁扣组件13用于锁定第一桨叶保护罩组件11与第二桨叶保护罩组件12，以保持第一桨叶保护罩组件11及第二桨叶保护罩组件12与无人飞行器100的卡合状态。
本实施例中，第一桨叶保护罩组件11和第二桨叶保护罩组件12设置于无人飞行器100的位置可为沿无人飞行器100的机身180的长轴方向的相对两侧，即图1所示的150和160。
在其他实施例中，第一桨叶保护罩组件11和第二桨叶保护罩组件12设置于无人飞行器100的位置还可为沿无人飞行器100的机身180的短轴方向的相对两侧。
本实施例中，第一桨叶保护罩组件11和第二桨叶保护罩组件12在 结构上完全对称，因此，在工艺制程上只需要一次开模，就可以做成两个桨叶保护罩组件，简化了制作工艺。此外还可使无人飞行器100的重心移动受桨叶保护罩组件的影响尽量小。
因此，本实施例通过将第一桨叶保护罩组件11和第二桨叶保护罩组件12分别设置在无人飞行器100的相对两侧，且分别与无人飞行器100的两侧卡合，由此在第一桨保护罩组件11和/或第二桨保护罩组件12收到撞击时，无人飞行器100可抵消部分撞击力，从而增强了第一桨叶保护罩组件11和第二桨叶保护罩组件12的稳定性，提高了第一桨叶保护罩组件11和第二桨叶保护罩组件12的抗冲击性能。
其中，锁扣组件13的锁定方式可为不可拆卸锁定方式，即将第一桨叶保护罩组件11和第二桨叶保护罩组件12以不可拆卸方式锁定连接。不可拆卸方式锁定连接可包括折边连接、铆钉连接、粘结连接和焊接连接等。本发明不对锁扣组件13的具体结构进行限制，只要实现上述的不可拆卸方式的锁定连接作用即可。不可拆卸的锁定连接方式可加强桨叶保护装置100的稳固性。
另一方面，考虑桨叶保护装置100在实际使用过程中，容易发生碰撞而导致其容易损坏，需要经常进行拆装，因此本发明为了使得桨叶保护装置100可进行快速拆装，将锁扣组件13设置为将第一桨叶保护罩组件11和第二桨叶保护罩组12件以可拆卸方式锁定连接。具体的，锁扣组件13包括第一锁扣主体131和第二锁扣主体132。第一锁扣主体131和第二锁扣主体132用于将第一桨叶保护罩组件11和第二桨叶保护罩组件12以可拆卸方式锁定连接。
其中，第一锁扣主体131固定设置于第一桨叶保护罩组件11上。第二锁扣主体132枢轴连接于第二桨叶保护罩组件12上，并能够相对于第二桨叶保护罩组件12枢轴转动成与第一锁扣主体131卡合固定。更具体的，第一锁扣主体131可为与第二锁扣主体132的枢轴方向平行设置的卡柱133，第二锁扣主体132包括枢轴1321和连接板1322，枢轴1321固定设置于第二桨叶保护罩组件12上。连接板1322和枢轴1321可拆卸连接。第二锁扣主体132上设置有与卡柱133对应的卡槽134。 具体为在连接板1322上设置有与卡柱133对应的卡槽134。因此，本实施例的锁扣组件13通过卡槽134和卡柱133即可实现可拆卸的连接，结构简单，并且重量轻巧，适合体积小的无人飞行器。
在其他实施例中，请参阅图4还可设置第一锁扣主体131为与第二锁扣主体132的枢轴方向平行设置的卡扣136，第二锁扣主体132上设置有与卡扣136对应的卡槽137。其中，卡扣136包括一勾状的扣合部138。在卡合过程中，卡槽137枢轴转动使卡扣136扣入卡槽137中，并且通过卡扣136的勾状扣合部138对卡槽137进行卡合。
请参阅图5，还可设置第一锁扣主体131为与第二锁扣主体132的枢轴方向平行设置的第一卡扣141，第二锁扣主体132上设置有与第一卡扣141对应的第二卡扣142。其中，第一卡扣141包括一勾状的第一扣合部143，第二卡扣142包括一勾状的第二扣合部144。在卡合过程中，第二卡扣142向第一卡扣141的方向枢轴转动，并通过第一扣合部143和第二扣合部144相互扣合。
请再参阅图1-图3所示，第二锁扣主体132上进一步设置有加强结构135，加强结构135可为相互交叉设置的凸起，用于加强第二锁扣主体132的强度。
进一步的，第一桨叶保护罩组件11包括彼此间隔设置的两个第一延伸臂111和112，第一锁扣主体131固定设置于两个第一延伸臂111和112之间。第二桨叶保护罩组件12还包括彼此间隔设置的两个第二延伸臂121和122，第二锁扣主体132枢轴连接于两个第二延伸臂121和122之间。具体的，第一锁扣主体131的卡柱固定设置于两个第一延伸臂111和112之间，第二锁扣主体132的枢轴1321枢轴连接于两个第二延伸臂121和122之间。
其中，第一延伸臂111和112自第一桨叶保护罩组件11向第二桨叶保护罩组件12的方向延伸，第二延伸臂121和122自第二桨叶保护罩组件12向第一桨叶保护罩组件11的方向延伸。
进一步的，第一延伸臂111和112还可与第二延伸臂121和122对位接插，具体而言，第一延伸臂111和112的端部和第二延伸臂121和 122的端部分别设置有对位接插结构113和123，以使第一桨叶保护罩组件11和第二桨叶保护罩组件12实现对位接插。其中，第一延伸臂111和112的端部为远离第一桨叶保护罩组件11的端部，同理，第二延伸臂121和122的端部为远离第二桨叶保护罩12的端部。
具体的，两个第一延伸臂111和112中的一个的端部设置有插柱114，两个第一延伸臂111和112中的另一个的端部设置有插孔115。如图1中所示，第一延伸臂111的端部设置有插柱114，第一延伸臂112的端部设置有插孔115。两个第二延伸臂121和122中的一个的端部设置有与插柱114接插配合的插孔，两个第二延伸臂121和122中的另一个的端部设置有与插孔115接插配合的插柱，如图1所示，第二延伸臂121的端部设置有与插柱114接插配合的插孔(图中未示出)，第二延伸臂122的端部设置有与插孔115接插配合的插柱124。
其中，插住114和124的规格大小以及插孔115和延伸臂121上的插孔的规格大小可为相同，使得在制造过程中可通过同一套模板既可形成，达到节省成本的目的。
在其他实施例中，还可以在两个第一延伸臂111和112的端部分别设置一个插柱，在两个第二延伸臂121和122的端部分别设置与插柱对应的插孔。或者在两个第一延伸臂111和112的端部分别设置一个插孔，在两个第二延伸臂121和122的端部分别设置与插孔对应的插柱。
进一步的，两个第一延伸臂111和112之间进一步设置有第一连接件1112，两个第二延伸臂121和122之间进一步设置有第二连接件1212。其中，第一连接件1112相对于卡柱133更靠近插柱114和插孔115设置。第二连接件1212相对于枢轴1321更靠近插柱124和第二插孔设置。
第一连接件1112和第二连接件1212用于分别加强第一延伸臂111和112以及第二延伸臂121和122的强度。
进一步的，第一桨叶保护罩组件11还包括间隔设置的第一上卡板116和第一下卡板117。第一上卡板116和第一下卡板117设置成在第一桨叶保护罩组件11和第二桨叶保护罩组件12分别与无人飞行器100的两侧卡合时分别卡持于无人飞行器100的两个相邻机臂101和102的上 表面和下表面上。
本实施例中，第一上卡板116和第一下卡板117卡持的无人飞行器100的两个相邻机臂可为沿无人飞行器100的机身180的长轴方向设置的并位于机身180的同一侧的两个相邻机臂，即图1所示的机臂101和102。
在其他实施例中，第一上卡板116和第一下卡板117卡持的无人飞行器100的两个相邻机臂还可为沿无人飞行器100的机身180的短轴方向设置的并位于机身180的同一侧的两个相邻机臂。即图1所示的机臂101和104或者机臂102和103。
第二桨叶保护罩组件12进一步包括间隔设置的第二上卡板125和第二下卡板126，第二上卡板125和第二下卡板126在第一桨叶保护罩组件11和第二桨叶保护罩组件12用于在第一桨叶保护罩组件11和第二桨叶保护罩组件12分别与无人飞行器100的两侧卡合时分别卡持于无人飞行器100的另外两个相邻机臂103和104的上表面和下表面上。
同理，本实施例中，第二上卡板125和第二下卡板126卡持的无人飞行器100的两个相邻机臂可为沿无人飞行器100的机身180的长轴方向设置的并位于机身180的同一侧的两个相邻机臂，即图1所示的机臂103和104。
在其他实施例中，第二上卡板125和第二下卡板126卡持的无人飞行器100的两个相邻机臂还可为沿无人飞行器100的机身180的短轴方向设置的并位于机身180的同一侧的两个相邻机臂。即图1所示的机臂101和104或者机臂102和103。
进一步的，第一桨叶保护罩组件11还包括连接于第一上卡板116和第一下卡板117的两个第一侧卡板118和119，两个第一侧卡板118和119用于在第一桨叶保护罩组件11和第二桨叶保护罩组件12分别与无人飞行器100的两侧卡合时分别卡持于两个相邻机臂101和102的相邻侧表面上。第二桨叶保护罩组件12进一步包括连接于第二上卡板125和第二下卡板126的两个第二侧卡板127和128，两个第二侧卡板127和128用于在第一桨叶保护罩组件11和第二桨叶保护罩组件12分别与 无人飞行器100的两侧卡合时分别卡持于另外两个相邻机臂103和104的相邻侧表面上。
本实施例中，上述所述的侧卡板均为倾斜设置，其倾斜的角度与其卡持的机臂的倾斜角度相对应。由此在侧卡板与机臂卡持时，其卡持的面可以无缝隙的贴合，从而得到更好的卡持固定作用。
进一步的，第一桨叶保护罩组件11还包括至少两个第一保护罩，至少两个第一保护罩固定连接或分开设置于第一延伸臂111和112。第二保护罩组件12包括至少两个第二保护罩，至少两个第二保护罩固定连接或分开设置于第二延伸臂121和122。
本实施例中，考虑到工艺的便利性以及保护罩的强度等问题，每个保护罩组件仅设置两个保护罩，即两个第一保护罩110和120以及两个第二保护罩130和140。其中，每个桨叶对应设置一个保护罩。具体设置如下文所述。
在其他实施例中，还可每个桨叶对应设置两个或以上的保护罩。
本实施例中，两个第一保护罩110和120设置于第一上卡板116上并进一步罩设于两个相邻机臂101和102上设置的桨叶105和106的外围。两个第一延伸臂111和112分别设置于两个第一保护罩110和120上。
进一步的，第一桨叶保护罩组件11还包括分别从第一保护罩110和120向下延伸的第一连接臂1101和1201，第一连接臂1101用于连接第一保护罩110和第一上卡板116，第一连接臂1201用于连接第一保护罩120和第一上卡板116。使得第一保护罩110和120设置于第一上卡板116上。
两个第二保护罩130和140设置于第二上卡板125上并进一步罩设于另外两个相邻机臂103和104上设置的桨叶107和108的外围，两个第二延伸臂121和122分别设置于两个第二保护罩130和140上。
同理，第二桨叶保护罩组件12还包括分别从第二保护罩130和140向下延伸的第二连接臂1301和1401，第二连接臂1301用于连接第二保护罩130和第二上卡板125，第二连接臂1401用于连接第二保护罩140 和第二上卡板125。使得第二保护罩130和140设置于第二上卡板125上。
在其他实施例中，还可以只设置第一下卡板117和第二下卡板126，第一下卡板117卡合在一侧机身的下表面上，第二下卡板126卡合在另一侧机身的下表面上。具体而言，第一下卡板117通过第一连接臂1101和1201分别与第一保护罩110和120连接，第二下卡板12通过第二连接臂1301和1401分别与第二保护罩130和140连接。
其中，第一下卡板117和第二下卡板126可沿机身的长轴方向设置，也可以沿机身的短轴方向设置。此外，在第一下卡板117和第二下卡板126沿机身的短轴方向设置时，可设置平行的两个第一下卡板117和两个第二下卡板126，其可沿机身的长轴方向间隔设置并卡合在机身沿长轴方向的两侧，由此可加强对卡合作用。
由前文所述可知，本实施例的第一保护罩110和120为沿无人飞行器100的机身180的长轴方向设置的并位于机身180的同一侧的两个相邻保护罩。同理，第二保护罩130和140也为沿无人飞行器100的机身180的长轴方向设置的并位于机身180的同一侧的两个相邻保护罩。其中，第一保护罩110以及120和第二保护罩130以及140分别设置在无人飞行器100的两对侧。本实施例中，第一延伸臂111和112分别自第一保护罩110和120向第二保护罩130和140的方向延伸，第二延伸臂121和122分别自第二保护罩130和140向第一保护罩110和120的方向延伸。使得在第一桨叶保护罩组件11和第二桨叶保护罩组件12分别与无人飞行器100的两侧卡合时，设置于两个第一延伸臂111和112之间的卡柱133和设置于两个第二延伸臂121和122之间的第二锁扣主体132的卡槽134可以在无人飞行器100的机身180中部进行卡合固定，由此提高了固定强度。
本实施例中，两个第一保护罩110和120固定连接设置于第一延伸臂111和112，两个第二保护罩130和140固定连接设置于第二延伸臂121和122。其中，两个第一保护罩110和120以及两个第二保护罩130和140可通过一体成型制成。在其他实施例中，还可以在第一保护罩110 和120之间以及第二保护罩130和140之间设置可拆卸元件，将第一保护罩110和120和第二保护罩130和140以可拆卸的方式连接。或者，在第一保护罩110和120之间以及第二保护罩130和140设置铰接结构，使得第一保护罩110和120以铰接的方式连接。
在其他实施例中，第一保护罩110和120以及第二保护罩130和140之间可以不相互连接。即第一保护罩110和120分开设置于第一延伸臂111和112，第二保护罩130和140分开设置于第二延伸臂121和122。
本实施例中，第一保护罩110和120以及第二保护罩130和140均为扇形罩体，并且扇形罩体的内部设置有用于加强扇形罩体强度的支撑臂170。支撑臂170的数量可以根据需要设置。支撑臂170一方面可对保护罩进行的强度进行加强，另一方面还可以在无人飞行器100撞上障碍物时对无人飞行器100进行保护。
本实施例中，扇形罩体可为270度设置，有利于无人飞行器的轻型化，还可以防止保护罩遮挡设置在无人飞行器上的摄像头或者其他视觉传感器。
在其他实施例中，扇形罩体的角度还可以设置为其他，只要不妨碍摄像头和其他视觉传感器的正常工作即可。进一步的，考虑到对保护罩的保护，还可以设置第一保护罩110和120以及第二保护罩130和140为圆形罩体结构。
综上所述，本发明可以对桨叶保护罩组件进行快速拆卸，方便更换，节约时间。此外，还增强了桨叶保护罩组件的稳定性，从而提高了桨叶保护罩组件的抗冲击性能。
以上所述仅为本发明的实施例，并非因此限制本发明的专利范围，凡是利用本发明说明书及附图内容所作的等效结构或等效流程变换，或直接或间接运用在其他相关的技术领域，均同理包括在本发明的专利保护范围内。

Claims (18)

  1. 一种无人飞行器的桨叶保护装置，其特征在于，所述桨叶保护装置包括第一桨叶保护罩组件、第二桨叶保护罩组件以及锁扣组件，其中所述第一桨叶保护罩组件和所述第二桨叶保护罩组件设置于所述无人飞行器的相对两侧，且分别与所述无人飞行器的两侧卡合，所述锁扣组件用于锁定所述第一桨叶保护罩组件与所述第二桨叶保护罩组件，以保持所述第一桨叶保护罩组件及所述第二桨叶保护罩组件与所述无人飞行器的卡合状态。
  2. 根据权利要求1所述的桨叶保护装置，其特征在于，所述锁扣组件包括第一锁扣主体和第二锁扣主体，所述第一锁扣主体和所述第二锁扣主体用于将所述第一桨叶保护罩组件和所述第二桨叶保护罩组件以可拆卸方式锁定连接。
  3. 根据权利要求2所述的桨叶保护装置，其特征在于，所述第一锁扣主体固定设置于所述第一桨叶保护罩组件上，所述第二锁扣主体枢轴连接于所述第二桨叶保护罩组件上，并能够相对于所述第二桨叶保护罩组件枢轴转动成与所述第一锁扣主体卡合固定。
  4. 根据权利要求3所述的桨叶保护装置，其特征在于，所述第二锁扣主体包括枢轴和连接板，所述枢轴固定设置于所述第二桨叶保护罩组件上。
  5. 根据权利要求4所述的桨叶保护装置，其特征在于，所述连接板和所述枢轴可拆卸连接。
  6. 根据权利要求4所述的桨叶保护装置，其特征在于，所述第一桨叶保护罩组件和所述第二桨叶保护罩组件呈中心对称结构。
  7. 根据权利要求3所述的桨叶保护装置，其特征在于，所述第一锁扣主体为与所述第二锁扣主体的枢轴方向平行设置的卡柱，所述第二锁扣主体上设置有与所述卡柱对应的卡槽。
  8. 根据权利要求3所述的桨叶保护装置，其特征在于，所述第一锁扣主体为与所述第二锁扣主体的枢轴方向平行设置的卡扣，所述第二锁 扣主体上设置有与所述卡扣对应的卡槽。
  9. 根据权利要求3所述的桨叶保护装置，其特征在于，所述第一锁扣主体为与所述第二锁扣主体的枢轴方向平行设置的第一卡扣，所述第二锁扣主体上设置有与所述第一卡扣对应的第二卡扣。
  10. 根据权利要求3所述的桨叶保护装置，其特征在于，所述第一桨叶保护罩组件包括彼此间隔设置的两个第一延伸臂，所述第一锁扣主体固定设置于所述两个第一延伸臂之间；
    所述第二桨叶保护罩组件包括彼此间隔设置的两个第二延伸臂，所述第二锁扣主体枢轴连接于所述两个第二延伸臂之间。
  11. 根据权利要求10所述的桨叶保护装置，其特征在于，所述第一延伸臂和所述第二延伸臂的端部设置有对位接插结构，以使所述第一桨叶保护罩组件和所述第二桨叶保护罩组件对位接插。
  12. 根据权利要求10所述的桨叶保护装置，其特征在于，两个所述第一延伸臂之间进一步设置有第一连接件，两个所述第二延伸臂之间进一步设置有第二连接件。
  13. 根据权利要求1所述的桨叶保护装置，其特征在于，所述第一桨叶保护罩组件进一步包括第一下卡板，所述第一下卡板卡合在所述无人飞行器的一侧机身的下表面；
    所述第二桨叶保护罩组件进一步包括第二下卡板，所述第二下卡板卡合在所述无人飞行器的另一侧机身的下表面上。
  14. 根据权利要求1所述的桨叶保护装置，其特征在于，所述第一桨叶保护罩组件进一步包括间隔设置的第一上卡板和第一下卡板，所述第一上卡板和第一下卡板设置成在所述第一桨叶保护罩组件和所述第二桨叶保护罩组件分别与所述无人飞行器的两侧卡合时分别卡持于所述无人飞行器的两个相邻机臂的上表面和下表面上，所述第二桨叶保护罩组件进一步包括间隔设置的第二上卡板和第二下卡板，所述第二上卡板和第二下卡板用于在所述第一桨叶保护罩组件和所述第二桨叶保护罩组件分别与所述无人飞行器的两侧卡合时分别卡持于所述无人飞行器的另外两个相邻机臂的上表面和下表面上。
  15. 根据权利要求14所述的桨叶保护装置，其特征在于，所述第一桨叶保护罩组件进一步包括连接于所述第一上卡板和所述第一下卡板的两个第一侧卡板，所述两个第一侧卡板分别卡持于所述两个相邻机臂的相邻侧表面上，所述第二桨叶保护罩组件进一步包括连接于所述第二上卡板和所述第二下卡板的两个第二侧卡板，所述两个第二侧卡板卡持于所述另外两个相邻机臂的相邻侧表面上。
  16. 根据权利要求10所述的桨叶保护罩装置，其特征在于，所述第一保护罩组件包括至少两个第一保护罩，所述至少两个第一保护罩固定连接或分开设置于所述第一延伸臂，所述第二保护罩组件包括至少两个第二保护罩，所述至少两个第二保护罩固定连接或分开设置于所述第二延伸臂。
  17. 根据权利要求16所述的桨叶保护装置，其特征在于，所述第一保护罩和所述第二保护罩为扇形罩体。
  18. 一种无人机系统，其特征在于，所述无人机系统包括如权利要求1-17任意一项所述的桨叶保护装置以及无人飞行器，所述桨叶保护装置锁扣于所述无人飞行器的机身上。
PCT/CN2017/090415 2017-05-19 2017-06-27 无人飞行器的桨叶保护装置及无人机系统 WO2018209765A1 (zh)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201780068011.5A CN109906185A (zh) 2017-05-19 2017-06-27 无人飞行器的桨叶保护装置及无人机系统

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201720566645.0 2017-05-19
CN201720566645.0U CN206954500U (zh) 2017-05-19 2017-05-19 无人飞行器的桨叶保护装置及无人机系统

Publications (1)

Publication Number Publication Date
WO2018209765A1 true WO2018209765A1 (zh) 2018-11-22

Family

ID=61375167

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2017/090415 WO2018209765A1 (zh) 2017-05-19 2017-06-27 无人飞行器的桨叶保护装置及无人机系统

Country Status (2)

Country Link
CN (2) CN206954500U (zh)
WO (1) WO2018209765A1 (zh)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN206954500U (zh) * 2017-05-19 2018-02-02 深圳市大疆创新科技有限公司 无人飞行器的桨叶保护装置及无人机系统
WO2021077252A1 (zh) * 2019-10-21 2021-04-29 深圳市大疆创新科技有限公司 桨叶保护装置及飞行器

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4856732A (en) * 1987-05-01 1989-08-15 Karl Eickmann Airborne vehicle with hydraulic drive and control
DE202005004698U1 (de) * 2005-03-23 2005-06-16 Dolch, Stefan, Dipl.-Ing. (FH) Kollisionsschutzvorrichtung eines Hubschraubers
CN204776022U (zh) * 2015-07-03 2015-11-18 安徽泽众安全科技有限公司 旋翼飞行器可拆卸防护装置
CN105775149A (zh) * 2016-02-29 2016-07-20 深圳市大疆创新科技有限公司 无人飞行器的保护罩、避障方法及无人飞行器
CN205418098U (zh) * 2015-11-30 2016-08-03 湖北易瓦特科技股份有限公司 避障旋翼无人机
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
CN205524952U (zh) * 2016-01-29 2016-08-31 深圳市大疆创新科技有限公司 无人机及其机臂机构
CN205707341U (zh) * 2016-07-01 2016-11-23 浙江智天科技有限公司 一种可拆卸的螺旋桨保护圈
CN304013301S (zh) * 2017-01-18

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9599992B2 (en) * 2014-06-23 2017-03-21 Nixie Labs, Inc. Launch-controlled unmanned aerial vehicles, and associated systems and methods
WO2016112124A2 (en) * 2015-01-08 2016-07-14 Vantage Robotics, Llc Unmanned aerial vehicle with propeller protection and high impact survivability
CN104608923B (zh) * 2015-01-31 2016-05-11 中南大学 一种蜂窝式六旋翼运输飞行器
KR101956535B1 (ko) * 2015-04-09 2019-03-11 주식회사 헬셀 로터부의 비상정지기능을 갖는 무인 비행체
CN205707325U (zh) * 2016-04-26 2016-11-23 普宙飞行器科技（深圳）有限公司 伸缩式桨叶驱动装置以及无人机
CN205952286U (zh) * 2016-08-19 2017-02-15 韩振铎 一种折叠机构及带折叠机构的无人机
CN206954500U (zh) * 2017-05-19 2018-02-02 深圳市大疆创新科技有限公司 无人飞行器的桨叶保护装置及无人机系统

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN304013301S (zh) * 2017-01-18
US4856732A (en) * 1987-05-01 1989-08-15 Karl Eickmann Airborne vehicle with hydraulic drive and control
DE202005004698U1 (de) * 2005-03-23 2005-06-16 Dolch, Stefan, Dipl.-Ing. (FH) Kollisionsschutzvorrichtung eines Hubschraubers
CN204776022U (zh) * 2015-07-03 2015-11-18 安徽泽众安全科技有限公司 旋翼飞行器可拆卸防护装置
CN205418098U (zh) * 2015-11-30 2016-08-03 湖北易瓦特科技股份有限公司 避障旋翼无人机
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
CN205524952U (zh) * 2016-01-29 2016-08-31 深圳市大疆创新科技有限公司 无人机及其机臂机构
CN105775149A (zh) * 2016-02-29 2016-07-20 深圳市大疆创新科技有限公司 无人飞行器的保护罩、避障方法及无人飞行器
CN205707341U (zh) * 2016-07-01 2016-11-23 浙江智天科技有限公司 一种可拆卸的螺旋桨保护圈

Also Published As

Publication number Publication date
CN206954500U (zh) 2018-02-02
CN109906185A (zh) 2019-06-18

Similar Documents

Publication Publication Date Title
US20170144753A1 (en) Rotor shrouding apparatus, supporting assembly, and unmanned aerial vehicle using the same
CN106687370B (zh) 旋翼组件及无人飞行器
WO2018209765A1 (zh) 无人飞行器的桨叶保护装置及无人机系统
KR20170101958A (ko) 완전 보호 무인기
EP3781477A1 (en) Unmanned aerial vehicle for mounting a clamp to a power line
CN103474595B (zh) 电池闩锁装置及对讲机
CN109073849A (zh) 镜头模组、云台系统及无人飞行器
EP1731355A1 (en) A chassis as well as an assembly comprising such a chassis
US20220324565A1 (en) Unmanned aerial vehicle
US20220227485A1 (en) Unmanned aerial vehicle folding landing gear
WO2018209708A1 (zh) 无人飞行器的桨叶保护罩及无人机系统
CN106697327B (zh) 飞机壁板对接结构
WO2023143199A1 (zh) 云台连接组件及无人机
CN105151129A (zh) 一种用于连接发动机盖与车身的连接组件
CN214740524U (zh) 一种易组装的门把手结构
CN205952311U (zh) 旋翼防护装置及无人多旋翼飞行器
CN205314684U (zh) 一种智能门锁前面板
CN210592415U (zh) 螺旋桨保护罩及飞行器
US20180111687A1 (en) Belly-mounted load beam for an aerial vehicle
CN211468775U (zh) 一种快拆结构及飞行器
CN113247235A (zh) 无人机
US20220267006A1 (en) Cargo hook assembly and helicopter
KR102623773B1 (ko) 드론 카메라 보호 커버
CN210618462U (zh) 一种用于无人机的保护机构
CN218898524U (zh) 安全帽头盔摄像头的固定支架

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 17910337

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 17910337

Country of ref document: EP

Kind code of ref document: A1