WO2019029387A1 - Aerial vehicle and arm assembly and frame thereof - Google Patents
Aerial vehicle and arm assembly and frame thereof Download PDFInfo
- Publication number
- WO2019029387A1 WO2019029387A1 PCT/CN2018/097520 CN2018097520W WO2019029387A1 WO 2019029387 A1 WO2019029387 A1 WO 2019029387A1 CN 2018097520 W CN2018097520 W CN 2018097520W WO 2019029387 A1 WO2019029387 A1 WO 2019029387A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- arm
- groove
- aircraft
- arm assembly
- frame
- Prior art date
Links
- 238000003825 pressing Methods 0.000 claims description 17
- 230000000712 assembly Effects 0.000 claims description 8
- 238000000429 assembly Methods 0.000 claims description 8
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 3
- 230000006835 compression Effects 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000005381 potential energy Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
-
- 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
- B64U30/293—Foldable or collapsible rotors or rotor supports
Definitions
- Embodiments of the present invention relate to the field of aircraft, and more particularly to an arm assembly of an aircraft, a frame, and an aircraft using the arm assembly or frame.
- An unmanned aerial vehicle generally includes a fuselage and a plurality of arms extending outward from the fuselage for supporting the power assembly at a predetermined position around the fuselage to drive the unmanned aerial vehicle to fly.
- the outwardly extending arm increases the volume of the UAV, which is not conducive to the storage and carrying of the UAV. In view of this, it is necessary to provide an arm assembly for an aircraft to solve the above problems.
- the technical problem to be solved by the embodiments of the present invention is to provide an arm assembly, a frame, and an aircraft using the arm assembly or the frame, which can realize stable folding and rapid deployment of the arm, and reduce the UAV in Volume in non-use state.
- a technical solution adopted by the present invention is to provide an arm assembly of an aircraft, including:
- a fixing base connected to the fuselage of the aircraft for locking the arm when the arm is in the folded position or the deployed position;
- An arm that is rotatably coupled to the mount such that the arm is rotatable relative to the mount between a folded position and a deployed position.
- the arm includes a pivotal connection with the fixed seat
- An end portion, the proximal end portion is provided with a first groove and a second groove;
- the elastic locking member includes a pressing block that engages with the first groove or the second groove and a resilient member for pressing the pressing piece into the first groove or the second groove;
- the pressing block is engaged with the first groove when the arm is in the folded position; the pressing block is engaged with the second concave when the arm is in the deployed position a slot; the resilient member is compressed when the arm is between the folded position and the deployed position.
- the first groove or the second groove is a circular arc groove
- the pressure block is a circular arc shaped pressure piece.
- the fixing base includes an upper wall, a lower wall opposite to the upper wall, and a side wall connecting the upper wall and the lower wall, the upper wall and the lower side
- the wall and the side wall enclose a receiving cavity, and the proximal end of the arm is disposed in the receiving cavity.
- the proximal end portion is provided with a mounting hole
- the arm assembly further includes a rotating connector that is disposed through the mounting hole and connected to the fixing base.
- the rotary joint includes a rotating shaft having an internally threaded hole and a screw threadedly coupled to the internally threaded hole, the rotating shaft passing through the mounting hole.
- the rotating connecting member is a rotating shaft, and two ends of the rotating shaft are respectively connected to the upper wall and the lower wall of the fixing base.
- the elastic locking member is mounted to the side wall.
- the arm when the arm is in the folded position, the arm is parallel to a sidewall of the fixing seat;
- the arm When the arm is in the deployed position, the arm is at a predetermined angle with a sidewall of the fixing seat.
- the present invention also provides a frame for an aircraft for solving the technical problems thereof, the frame including a body and a boom assembly as described above connected to the body.
- two sets of the arm assemblies are disposed on the same side of the fuselage, and the two sets of arms on the same side of the fuselage are in a folded state when the rack is in a folded state.
- the arms of the assembly are different in height from the bottom of the fuselage.
- the present invention also provides an aircraft for solving the technical problems thereof, the aircraft comprising a frame as described above and a flight control module mounted inside the frame.
- the utility model has the beneficial effects that the arm assembly of the aircraft of the embodiment of the invention comprises an elastic locking member, a fixing base and an arm, wherein the arm is rotatably connected with the fixing seat, and the elastic locking member is connected with the fixing seat. It is used to lock the arm when the arm is in the folded position or the unfolded position, which can realize the stable folding and rapid deployment of the arm, and reduce the volume of the UAV in the non-use state.
- FIG. 1 is a structural exploded view of an arm assembly of an aircraft according to an embodiment of the present invention
- Figure 2 is a schematic view of the arm of the arm assembly shown in Figure 1 in a folded position
- Figure 3 is a schematic view of the arm of the arm assembly shown in Figure 1 in a deployed position
- FIG. 4 is a schematic view of the aircraft of the embodiment of the present invention in an unfolded state
- Figure 5 is a schematic view of the aircraft of the embodiment of the present invention when the frame of the aircraft is in a folded state;
- Figure 6 is another schematic view of the aircraft of the embodiment of the present invention when the frame of the aircraft is in a folded state
- Fig. 7 is still another schematic view of the aircraft of the embodiment of the present invention when the frame of the aircraft is in a folded state.
- FIG. 1 is an exploded view of an arm assembly of an aircraft according to an embodiment of the present invention.
- the arm assembly 10 includes an elastic locking member 100 , a fixing base 200 , and an arm 300 .
- the arm 300 is rotatably coupled to the fixed base 200 such that the arm 300 is rotatable relative to the fixed seat 200 between the folded position and the deployed position.
- the elastic locking member 100 is mounted to the fixed base 200 for being placed at the arm 300.
- the arm 300 is locked in the folded or deployed position.
- the arm 300 includes a proximal end 310 that is rotationally coupled to the mount 200 and a distal end 320 that is remote from the proximal end 310.
- the end of the distal end portion 320 is provided with a power assembly (not shown) for driving the aircraft to move, such as driving the aircraft to take off, land, hover, change direction, speed, orientation, and the like.
- the mount 200 includes an upper wall 210, a lower wall 220 disposed opposite the upper wall 210, and a side wall 230 connecting the upper wall 210 and the lower wall 220.
- the upper wall 210, the lower wall 220, and the side wall 230 are disposed to form a receiving cavity 240.
- the proximal end portion 310 of the arm 300 and the fixing base 200 is rotatably disposed in the accommodating cavity 240.
- the proximal end portion 310 of the arm 300 is provided with a mounting hole 311 through which the mounting hole 311 passes.
- the arm assembly 10 further includes a rotary connector that is disposed through the mounting hole 311.
- the rotary connector is fixed to the upper wall 210 and/or the lower wall 220 of the mount 200 to rotatably mount the arm 300 to the mount 200.
- the rotary joint includes a rotating shaft 410 provided with an internally threaded hole and a screw 420 threadedly coupled to the internally threaded hole.
- the rotating shaft 410 is threadedly connected to the screw 420 after passing through the mounting hole 311.
- the rotary joint may also include only the rotating shaft, and the two ends of the rotating shaft are respectively connected to the upper wall 210 and the lower wall 220 of the fixed base 200.
- the proximal end portion 310 is provided with a first recess 312 and a second recess 313 .
- the elastic locking member 100 is mounted to the side wall 230 of the fixing base 200.
- the elastic locking member 100 includes a baffle 130 connected to the side wall 230 of the fixing base 200, a pressing block 110 engaged with the first groove 312 or the second groove 313, and a pressing block 110 for pressing the pressing block 110 into the first A recess 312 or a resilient element 120 in the second recess 313.
- the elastic member 120 has one end connected to the pressing block 110 and the other end connected to the baffle 130. When the arm 300 is between the folded position and the deployed position, the resilient member 120 is compressed.
- the other end of the elastic member 120 can also be directly fixed to the fixing base 200.
- the elastic member 120 is a compression spring, and a cylindrical pin can be disposed on the fixing seat, and the other end of the compression spring is sleeved on the cylinder.
- the elastic member 120 is a reset elastic piece, and the reset elastic piece can be fixed on the fixing base 200 by adhesive or welding.
- the clamp 110 when the arm 300 is in the folded position, the clamp 110 is engaged with the first recess 312 to securely hold the arm 300 in the folded position.
- the clamp 110 when the arm 300 is in the deployed position, the clamp 110 is engaged with the second recess 313 to securely hold the arm 300 in the deployed position.
- the arm 300 when the arm 300 is in the folded position, the arm 300 is parallel to the side wall 230 of the fixing base 200; when the arm 300 is in the deployed position, the arm 300 is at a predetermined angle with the side wall 230 of the fixing base 200, Such as 0°, 30°, 45° or 60°.
- the arm 300 when the aircraft does not need to fly, the arm 300 is held in the folded position to facilitate storage, carrying or transportation of the aircraft.
- the elastic potential energy stored by the elastic member 120 due to the compression can clamp the pressing block 110 to the concave corresponding to the position.
- the pressing block 110 is engaged with the first groove 312 of the arm 300, and the arm 300 is rotated from the folded position to the deployed position after being subjected to an external force in a certain direction, the elastic member.
- the 120 is compressed, and when the arm 300 is rotated to the deployed position, the elastic force of the elastic member 120 enables the clamp 110 to snap into the second recess 313 of the arm 300.
- the bottom of the first groove 312 or the second groove 313 of the arm 300 is a circular arc groove, correspondingly, with the first groove 312 or the second groove 313
- the head of the combined compact 110 is also arcuate.
- the number of the first groove 312 or the second groove 313 may be one or more.
- the corresponding pressure block The number of the 110 and the elastic members 120 connected to the compact 110 is also plural.
- the arm assembly of the aircraft of the embodiment includes the elastic locking member 100, the fixing base 200 and the arm 300.
- the arm 300 is rotatably connected with the fixing base 200, and the elastic locking member 100 and the fixing seat are fixed.
- the 200 fixed connection is used to lock the arm 300 when the arm 300 is in the folded position or the deployed position, which can achieve stable folding and rapid deployment of the arm, and reduce the volume of the UAV in the non-use state.
- the embodiment of the invention further provides a frame of an aircraft, comprising a fuselage 20 and the arm assembly 10 as described above, wherein the fixed base 200 of the arm assembly 10 can be part of the fuselage 20 or independent of the machine
- the body 20 is fixedly connected to the body 20.
- the specific shape and structure of the airframe 20 are not limited in this embodiment, and those skilled in the art can set according to specific requirements.
- the number of the arm assemblies 10 can also be set according to specific requirements, such as two, three, four, six, etc., two or more sets of arm assemblies 10 along the center of the fuselage 20 Symmetrically disposed on the body 20.
- the following embodiment is described by taking a rack including four sets of arm assemblies 10 as an example.
- FIG. 4 is a schematic view of the aircraft frame in an unfolded state
- FIGS. 5-7 are schematic views of the aircraft frame in a folded state.
- the same side of the fuselage 20 is oppositely provided with two sets of arm assemblies 10, and when the rack is in a folded state, the arms 300 of the two sets of arm assemblies 10 are different in height from the bottom of the body 20.
- the frame When the frame is folded, the frame has the smallest lateral dimension and a more compact structure, as shown in Figure 5.
- Embodiments of the present invention also provide an unmanned aerial vehicle including a rack as described above and a flight control module mounted inside the rack.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Pivots And Pivotal Connections (AREA)
- Seats For Vehicles (AREA)
Abstract
An aircraft and an arm assembly (10) and frame thereof, the arm assembly (10) comprising: an elastic locking member (100), a fixing seat (200) and an arm (300); the arm (300) is rotatably connected to the fixing seat (200) such that the arm (300) may rotate relative to the fixing seat (200) between a folding position and an unfolding position; the elastic locking member (100) is connected to the fixing seat (200), being used for locking the arm (300) when the arm (300) is in the folding position or unfolding position. By means of the foregoing manner, stable folding and rapid unfolding of the arm may be achieved, thus reducing the volume of an unused unmanned aerial vehicle.
Description
本发明实施例涉及飞行器领域,特别是涉及一种飞行器的机臂组件、机架及使用该机臂组件或机架的飞行器。Embodiments of the present invention relate to the field of aircraft, and more particularly to an arm assembly of an aircraft, a frame, and an aircraft using the arm assembly or frame.
随着科技的发展,无人飞行器技术越来越成熟,无人飞行器常被用于执行航拍、监测、勘探等任务。无人飞行器通常包括机身以及从机身向外伸展的多个机臂,机臂用于将动力组件支撑于机身周围预定位置处,以带动无人飞行器飞行。With the development of science and technology, unmanned aerial vehicle technology is becoming more and more mature, and unmanned aerial vehicles are often used to perform tasks such as aerial photography, monitoring, and exploration. An unmanned aerial vehicle generally includes a fuselage and a plurality of arms extending outward from the fuselage for supporting the power assembly at a predetermined position around the fuselage to drive the unmanned aerial vehicle to fly.
在无人飞行器处于非使用状态下时,向外伸展的机臂增加了无人飞行器的体积,不利于无人飞行器的存放及携带。有鉴于此,有必要提供一种飞行器的机臂组件,以解决上述问题。When the UAV is not in use, the outwardly extending arm increases the volume of the UAV, which is not conducive to the storage and carrying of the UAV. In view of this, it is necessary to provide an arm assembly for an aircraft to solve the above problems.
发明内容Summary of the invention
本发明实施例主要解决的技术问题是提供一种飞行器的机臂组件、机架及使用该机臂组件或机架的飞行器,能够实现机臂的稳固折叠和快速展开,减小无人飞行器在非使用状态下的体积。The technical problem to be solved by the embodiments of the present invention is to provide an arm assembly, a frame, and an aircraft using the arm assembly or the frame, which can realize stable folding and rapid deployment of the arm, and reduce the UAV in Volume in non-use state.
为解决上述技术问题,本发明采用的一个技术方案是:提供一种飞行器的机臂组件,包括:In order to solve the above technical problem, a technical solution adopted by the present invention is to provide an arm assembly of an aircraft, including:
固定座,与所述飞行器的机身相连,用于在所述机臂处于所述折叠位置或所述展开位置时锁紧所述机臂;a fixing base connected to the fuselage of the aircraft for locking the arm when the arm is in the folded position or the deployed position;
弹性锁紧件,安装于所述固定座;以及a resilient locking member mounted to the mount;
机臂,所述机臂与所述固定座转动连接,以使所述机臂可相对所述固定座在折叠位置与展开位置之间旋转。An arm that is rotatably coupled to the mount such that the arm is rotatable relative to the mount between a folded position and a deployed position.
在本发明的一实施例中,所述机臂包括与所述固定座转动连接的近In an embodiment of the invention, the arm includes a pivotal connection with the fixed seat
端部,所述近端部设置有第一凹槽和第二凹槽;An end portion, the proximal end portion is provided with a first groove and a second groove;
所述弹性锁紧件包括与所述第一凹槽或第二凹槽卡合的压块和用于将所述压块压入所述第一凹槽或第二凹槽内的弹性元件;The elastic locking member includes a pressing block that engages with the first groove or the second groove and a resilient member for pressing the pressing piece into the first groove or the second groove;
当所述机臂处于所述折叠位置时,所述压块卡合于所述第一凹槽;当所述机臂处于所述展开位置时,所述压块卡合于所述第二凹槽;当所述机臂处于所述折叠位置与所述展开位置之间时,所述弹性元件被压缩。The pressing block is engaged with the first groove when the arm is in the folded position; the pressing block is engaged with the second concave when the arm is in the deployed position a slot; the resilient member is compressed when the arm is between the folded position and the deployed position.
在本发明的一实施例中,所述第一凹槽或所述第二凹槽为圆弧槽,所述压块为圆弧形的压块。In an embodiment of the invention, the first groove or the second groove is a circular arc groove, and the pressure block is a circular arc shaped pressure piece.
在本发明的一实施例中,所述固定座包括上壁、与所述上壁相对设置的下壁以及连接所述上壁和所述下壁的侧壁,所述上壁、所述下壁和所述侧壁围设形成一容置腔,所述机臂的所述近端部设置于所述容置腔内。In an embodiment of the invention, the fixing base includes an upper wall, a lower wall opposite to the upper wall, and a side wall connecting the upper wall and the lower wall, the upper wall and the lower side The wall and the side wall enclose a receiving cavity, and the proximal end of the arm is disposed in the receiving cavity.
在本发明的一实施例中,所述近端部设置有安装孔;In an embodiment of the invention, the proximal end portion is provided with a mounting hole;
所述机臂组件还包括穿设于所述安装孔并于所述固定座相连的转动连接件。The arm assembly further includes a rotating connector that is disposed through the mounting hole and connected to the fixing base.
在本发明的一实施例中,所述转动连接件包括具有内螺纹孔的转轴和与所述内螺纹孔螺纹连接的螺钉,所述转轴穿设于所述安装孔。In an embodiment of the invention, the rotary joint includes a rotating shaft having an internally threaded hole and a screw threadedly coupled to the internally threaded hole, the rotating shaft passing through the mounting hole.
在本发明的一实施例中,所述转动连接件为转轴,所述转轴的两端分别与所述固定座的上壁和下壁相连。In an embodiment of the invention, the rotating connecting member is a rotating shaft, and two ends of the rotating shaft are respectively connected to the upper wall and the lower wall of the fixing base.
在本发明的一实施例中,所述弹性锁紧件安装于所述侧壁。In an embodiment of the invention, the elastic locking member is mounted to the side wall.
在本发明的一实施例中,在所述机臂处于所述折叠位置时,所述机臂与所述固定座的侧壁平行;In an embodiment of the invention, when the arm is in the folded position, the arm is parallel to a sidewall of the fixing seat;
在所述机臂处于所述展开位置时,所述机臂与所述固定座的侧壁成预设夹角。When the arm is in the deployed position, the arm is at a predetermined angle with a sidewall of the fixing seat.
本发明为解决其技术问题还提供了一种飞行器的机架,所述机架包括机身和与所述机身相连的如上述所述的机臂组件。The present invention also provides a frame for an aircraft for solving the technical problems thereof, the frame including a body and a boom assembly as described above connected to the body.
在本发明的一实施例中,所述机身的同一侧设置有两组所述机臂组件,在所述机架处于折叠状态时,位于所述机身同一侧的所述两组机臂组件的机臂相较于所述机身底部的高度不相同。In an embodiment of the invention, two sets of the arm assemblies are disposed on the same side of the fuselage, and the two sets of arms on the same side of the fuselage are in a folded state when the rack is in a folded state. The arms of the assembly are different in height from the bottom of the fuselage.
本发明为解决其技术问题还提供了一种飞行器,所述飞行器包括如上述所述的机架和安装于所述机架内部的飞行控制模块。The present invention also provides an aircraft for solving the technical problems thereof, the aircraft comprising a frame as described above and a flight control module mounted inside the frame.
本发明实施例的有益效果是:本发明实施例的飞行器的机臂组件包括弹性锁紧件、固定座以及机臂,其中,机臂与固定座转动连接,弹性锁紧件与固定座连接,用于在机臂处于折叠位置或展开位置时锁紧机臂,能够实现机臂的稳固折叠和快速展开,减小无人飞行器在非使用状态下的体积。The utility model has the beneficial effects that the arm assembly of the aircraft of the embodiment of the invention comprises an elastic locking member, a fixing base and an arm, wherein the arm is rotatably connected with the fixing seat, and the elastic locking member is connected with the fixing seat. It is used to lock the arm when the arm is in the folded position or the unfolded position, which can realize the stable folding and rapid deployment of the arm, and reduce the volume of the UAV in the non-use state.
一个或多个实施例通过与之对应的附图中的图片进行示例性说明,这些示例性说明并不构成对实施例的限定,附图中具有相同参考数字标号的元件表示为类似的元件,除非有特别申明,附图中的图不构成比例限制。The one or more embodiments are exemplified by the accompanying drawings in the accompanying drawings, and FIG. The figures in the drawings do not constitute a scale limitation unless otherwise stated.
图1是本发明实施例的飞行器的机臂组件的结构分解图;1 is a structural exploded view of an arm assembly of an aircraft according to an embodiment of the present invention;
图2是图1所示的机臂组件的机臂处于折叠位置时的示意图;Figure 2 is a schematic view of the arm of the arm assembly shown in Figure 1 in a folded position;
图3是图1所示的机臂组件的机臂处于展开位置时的示意图;Figure 3 is a schematic view of the arm of the arm assembly shown in Figure 1 in a deployed position;
图4是本发明实施例的飞行器的机架处于展开状态时的示意图;4 is a schematic view of the aircraft of the embodiment of the present invention in an unfolded state;
图5是本发明实施例的飞行器的机架处于折叠状态时的示意图;Figure 5 is a schematic view of the aircraft of the embodiment of the present invention when the frame of the aircraft is in a folded state;
图6是本发明实施例的飞行器的机架处于折叠状态时的另一示意图;Figure 6 is another schematic view of the aircraft of the embodiment of the present invention when the frame of the aircraft is in a folded state;
图7是本发明实施例的飞行器的机架处于折叠状态时的又一示意图。Fig. 7 is still another schematic view of the aircraft of the embodiment of the present invention when the frame of the aircraft is in a folded state.
为了便于理解本发明,下面结合附图和具体实施例,对本发明进行更详细的说明。需要说明的是,当元件被表述“固定于”另一个元件,它可以直接在另一个元件上、或者其间可以存在一个或多个居中的元件。当一个元件被表述“连接”另一个元件,它可以是直接连接到另一个元件、或者其间可以存在一个或多个居中的元件。本说明书所使用的术语“垂直的”、“水平的”、“左”、“右”以及类似的表述只是为了说明的目的。In order to facilitate the understanding of the present invention, the present invention will be described in more detail below with reference to the accompanying drawings and specific embodiments. It is to be noted that when an element is described as being "fixed" to another element, it can be directly on the other element or one or more of the elements in the middle. When an element is referred to as "connected" to another element, it can be a <RTI ID=0.0> </ RTI> </ RTI> <RTIgt; The terms "vertical," "horizontal," "left," "right," and the like, as used in this specification, are for the purpose of illustration.
除非另有定义,本说明书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。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,不是用于限制本发明。本说明书所使用的术语“和/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。Unless otherwise defined, all technical and scientific terms used in the specification are the same meaning The terms used in the description of the present invention are for the purpose of describing the specific embodiments and are not intended to limit the invention. The term "and/or" used in this specification includes any and all combinations of one or more of the associated listed items.
请参阅图1,图1为本发明实施例提供的飞行器的机臂组件的结构分解图,如图1所示,该机臂组件10包括:弹性锁紧件100、固定座200以及机臂300。其中,机臂300与固定座200转动连接,以使机臂300可相对固定座200在折叠位置与展开位置之间旋转,弹性锁紧件100安装于固定座200,用于在机臂300处于折叠位置或展开位置时锁紧机臂300。Referring to FIG. 1 , FIG. 1 is an exploded view of an arm assembly of an aircraft according to an embodiment of the present invention. As shown in FIG. 1 , the arm assembly 10 includes an elastic locking member 100 , a fixing base 200 , and an arm 300 . . The arm 300 is rotatably coupled to the fixed base 200 such that the arm 300 is rotatable relative to the fixed seat 200 between the folded position and the deployed position. The elastic locking member 100 is mounted to the fixed base 200 for being placed at the arm 300. The arm 300 is locked in the folded or deployed position.
机臂300包括与固定座200转动连接的近端部310,以及远离近端部310的远端部320。远端部320的末端设有动力组件(图未示出),动力组件用于带动飞行器移动,如带动飞行器起飞、降落、盘旋、改变方向、速度、方位等。The arm 300 includes a proximal end 310 that is rotationally coupled to the mount 200 and a distal end 320 that is remote from the proximal end 310. The end of the distal end portion 320 is provided with a power assembly (not shown) for driving the aircraft to move, such as driving the aircraft to take off, land, hover, change direction, speed, orientation, and the like.
固定座200包括上壁210、与上壁210相对设置的下壁220以及连接上壁210和下壁220的侧壁230。上壁210、下壁220和侧壁230围设形成一容置腔240,机臂300与固定座200转动连接的近端部310设置于容置腔240内。The mount 200 includes an upper wall 210, a lower wall 220 disposed opposite the upper wall 210, and a side wall 230 connecting the upper wall 210 and the lower wall 220. The upper wall 210, the lower wall 220, and the side wall 230 are disposed to form a receiving cavity 240. The proximal end portion 310 of the arm 300 and the fixing base 200 is rotatably disposed in the accommodating cavity 240.
机臂300的近端部310设置有安装孔311,安装孔311贯通近端不310。机臂组件10还包括穿设于安装孔311的转动连接件,转动连接件与固定座200的上壁210和/或下壁220固定,以将机臂300转动安装于固定座200上。在本实施例中,转动连接件包括设有内螺纹孔的转轴410和与内螺纹孔螺纹连接的螺钉420。转轴410贯穿安装孔311后与螺钉420螺纹连接。在其他实施例中,转动连接件也可以仅包括转轴,该转轴的两端分别与固定座200的上壁210和下壁220相连。The proximal end portion 310 of the arm 300 is provided with a mounting hole 311 through which the mounting hole 311 passes. The arm assembly 10 further includes a rotary connector that is disposed through the mounting hole 311. The rotary connector is fixed to the upper wall 210 and/or the lower wall 220 of the mount 200 to rotatably mount the arm 300 to the mount 200. In the present embodiment, the rotary joint includes a rotating shaft 410 provided with an internally threaded hole and a screw 420 threadedly coupled to the internally threaded hole. The rotating shaft 410 is threadedly connected to the screw 420 after passing through the mounting hole 311. In other embodiments, the rotary joint may also include only the rotating shaft, and the two ends of the rotating shaft are respectively connected to the upper wall 210 and the lower wall 220 of the fixed base 200.
请参阅图2和图3,近端部310设置有第一凹槽312和第二凹槽313。在本发明的一实施例中,弹性锁紧件100安装于固定座200的侧壁230。弹性锁紧件100包括与所述固定座200的侧壁230相连的挡板130、与 第一凹槽312或第二凹槽313卡合的压块110以及用于将压块110压入第一凹槽312或第二凹槽313内的弹性元件120。弹性元件120一端与压块110相连,另一端与挡板130相连。当机臂300处于折叠位置和展开位置之间时,弹性元件120被压缩。其他实施例中,弹性元件120的另一端也可以直接固定于固定座200,如,弹性元件120为压簧,可在固定座上设置一圆柱销,将压簧的另一端套设于该圆柱销上;又如,弹性元件120为复位弹片,可通过背胶或焊接的方式将复位弹片固定在固定座200上。Referring to FIGS. 2 and 3 , the proximal end portion 310 is provided with a first recess 312 and a second recess 313 . In an embodiment of the invention, the elastic locking member 100 is mounted to the side wall 230 of the fixing base 200. The elastic locking member 100 includes a baffle 130 connected to the side wall 230 of the fixing base 200, a pressing block 110 engaged with the first groove 312 or the second groove 313, and a pressing block 110 for pressing the pressing block 110 into the first A recess 312 or a resilient element 120 in the second recess 313. The elastic member 120 has one end connected to the pressing block 110 and the other end connected to the baffle 130. When the arm 300 is between the folded position and the deployed position, the resilient member 120 is compressed. In other embodiments, the other end of the elastic member 120 can also be directly fixed to the fixing base 200. For example, the elastic member 120 is a compression spring, and a cylindrical pin can be disposed on the fixing seat, and the other end of the compression spring is sleeved on the cylinder. On the pin; for example, the elastic member 120 is a reset elastic piece, and the reset elastic piece can be fixed on the fixing base 200 by adhesive or welding.
如图2所示,在机臂300处于折叠位置时,压块110卡合于第一凹槽312,以使机臂300稳固保持在该折叠位置。如图3所示,在机臂300处于展开位置时,压块110卡合于第二凹槽313,以使机臂300稳固保持在该展开位置。其中,在机臂300处于折叠位置时,机臂300与固定座200的侧壁230平行;在机臂300处于展开位置时,机臂300与固定座200的侧壁230成预设夹角,如0°、30°、45°或60°。如此,当飞行器不需飞行时,将机臂300保持在该折叠位置,便于飞行器的收纳、携带或运输。As shown in FIG. 2, when the arm 300 is in the folded position, the clamp 110 is engaged with the first recess 312 to securely hold the arm 300 in the folded position. As shown in FIG. 3, when the arm 300 is in the deployed position, the clamp 110 is engaged with the second recess 313 to securely hold the arm 300 in the deployed position. Wherein, when the arm 300 is in the folded position, the arm 300 is parallel to the side wall 230 of the fixing base 200; when the arm 300 is in the deployed position, the arm 300 is at a predetermined angle with the side wall 230 of the fixing base 200, Such as 0°, 30°, 45° or 60°. As such, when the aircraft does not need to fly, the arm 300 is held in the folded position to facilitate storage, carrying or transportation of the aircraft.
当机臂300相对固定座200在从折叠位置和展开位置之一位置旋转至另一位置时,弹性元件120由于被压缩而储存的弹性势能可将压块110卡入至与该位置对应的凹槽中。例如,当机臂300处于折叠位置时,压块110与机臂300的第一凹槽312卡合,机臂300受到一定方向的外力后相对固定座200从折叠位置向展开位置旋转,弹性元件120被压缩,当机臂300旋转至展开位置时,弹性元件120的弹性力能够使得压块110卡入机臂300的第二凹槽313。When the arm 300 is rotated relative to the fixed seat 200 from one of the folded position and the deployed position to another position, the elastic potential energy stored by the elastic member 120 due to the compression can clamp the pressing block 110 to the concave corresponding to the position. In the slot. For example, when the arm 300 is in the folded position, the pressing block 110 is engaged with the first groove 312 of the arm 300, and the arm 300 is rotated from the folded position to the deployed position after being subjected to an external force in a certain direction, the elastic member. The 120 is compressed, and when the arm 300 is rotated to the deployed position, the elastic force of the elastic member 120 enables the clamp 110 to snap into the second recess 313 of the arm 300.
为方便使机臂300相对固定座200转动,机臂300的第一凹槽312或第二凹槽313的底部为圆弧槽,对应地,与第一凹槽312或第二凹槽313卡合的压块110的头部也为圆弧形。In order to facilitate the rotation of the arm 300 relative to the fixed base 200, the bottom of the first groove 312 or the second groove 313 of the arm 300 is a circular arc groove, correspondingly, with the first groove 312 or the second groove 313 The head of the combined compact 110 is also arcuate.
本领域技术人员应当理解,第一凹槽312或第二凹槽313的数量可以为一个或多个,当第一凹槽312或第二凹槽313的数量为多个时,对应的压块110以及与压块110连接的弹性元件120的数量也为多个。It should be understood by those skilled in the art that the number of the first groove 312 or the second groove 313 may be one or more. When the number of the first groove 312 or the second groove 313 is plural, the corresponding pressure block The number of the 110 and the elastic members 120 connected to the compact 110 is also plural.
区别于现有技术,本实施例的飞行器的机臂组件包括弹性锁紧件100、固定座200以及机臂300,其中,机臂300与固定座200转动连接,弹性锁紧件100与固定座200固定连接,用于在机臂300处于折叠位置或展开位置时锁紧机臂300,能够实现机臂的稳固折叠和快速展开,减小无人飞行器在非使用状态下的体积。Different from the prior art, the arm assembly of the aircraft of the embodiment includes the elastic locking member 100, the fixing base 200 and the arm 300. The arm 300 is rotatably connected with the fixing base 200, and the elastic locking member 100 and the fixing seat are fixed. The 200 fixed connection is used to lock the arm 300 when the arm 300 is in the folded position or the deployed position, which can achieve stable folding and rapid deployment of the arm, and reduce the volume of the UAV in the non-use state.
本发明实施例还提供一种飞行器的机架,包括机身20和如上所述的机臂组件10,其中,机臂组件10的固定座200可为机身20的一部分,也可独立于机身20,而与机身20固定连接。The embodiment of the invention further provides a frame of an aircraft, comprising a fuselage 20 and the arm assembly 10 as described above, wherein the fixed base 200 of the arm assembly 10 can be part of the fuselage 20 or independent of the machine The body 20 is fixedly connected to the body 20.
本实施例对于机身20的具体形状结构不作限定,本领域技术人员可根据具体的需求进行设置。同样地,机臂组件10的个数也可根据具体的需求进行设置,如设置两组、三组、四组、六组等,两组或多组机臂组件10沿机身20的中心位置对称设置在机身20上。为便于描述,如下实施例以包括四组机臂组件10的机架为例进行说明。The specific shape and structure of the airframe 20 are not limited in this embodiment, and those skilled in the art can set according to specific requirements. Similarly, the number of the arm assemblies 10 can also be set according to specific requirements, such as two, three, four, six, etc., two or more sets of arm assemblies 10 along the center of the fuselage 20 Symmetrically disposed on the body 20. For convenience of description, the following embodiment is described by taking a rack including four sets of arm assemblies 10 as an example.
请参阅图4,图4为飞行器的机架处于展开状态时的示意图,图5-图7为飞行器的机架处于折叠状态时的示意图。较为优选地,机身20的同一侧相对设置有两组机臂组件10,在机架处于折叠状态时,两组机臂组件10的机臂300相较于机身20底部的高度不相同,使得机架处于折叠状态时,机架的横向尺寸最小,结构更加紧凑,如图5所示。Please refer to FIG. 4. FIG. 4 is a schematic view of the aircraft frame in an unfolded state, and FIGS. 5-7 are schematic views of the aircraft frame in a folded state. Preferably, the same side of the fuselage 20 is oppositely provided with two sets of arm assemblies 10, and when the rack is in a folded state, the arms 300 of the two sets of arm assemblies 10 are different in height from the bottom of the body 20. When the frame is folded, the frame has the smallest lateral dimension and a more compact structure, as shown in Figure 5.
本发明实施例还提供一种无人飞行器,无人飞行器包括如上所述的机架和安装于机架内部的飞行控制模块。Embodiments of the present invention also provide an unmanned aerial vehicle including a rack as described above and a flight control module mounted inside the rack.
需要说明的是,本发明的说明书及其附图中给出了本发明的较佳的实施例,但是,本发明可以通过许多不同的形式来实现,并不限于本说明书所描述的实施例,这些实施例不作为对本发明内容的额外限制,提供这些实施例的目的是使对本发明的公开内容的理解更加透彻全面。并且,上述各技术特征继续相互组合,形成未在上面列举的各种实施例,均视为本发明说明书记载的范围;进一步地,对本领域普通技术人员来说,可以根据上述说明加以改进或变换,而所有这些改进和变换都应属于本发明所附权利要求的保护范围。It is to be noted that the preferred embodiments of the present invention are described in the specification of the present invention, and the present invention may be embodied in many different forms and not limited to the embodiments described herein. These examples are not intended to be limiting as to the scope of the present invention, which is intended to provide a more thorough understanding of the present disclosure. Further, the above various technical features are further combined with each other to form various embodiments not enumerated above, and are considered as the scope of the description of the present invention; further, those skilled in the art can improve or change according to the above description. All such improvements and modifications are intended to be included within the scope of the appended claims.
Claims (12)
- 一种飞行器的机臂组件,其特征在于,包括:An arm assembly for an aircraft, comprising:固定座,与所述飞行器的机身相连,用于在所述机臂处于所述折叠位置或所述展开位置时锁紧所述机臂;a fixing base connected to the fuselage of the aircraft for locking the arm when the arm is in the folded position or the deployed position;弹性锁紧件,安装于所述固定座;以及a resilient locking member mounted to the mount;机臂,所述机臂与所述固定座转动连接,以使所述机臂可相对所述固定座在折叠位置与展开位置之间旋转。An arm that is rotatably coupled to the mount such that the arm is rotatable relative to the mount between a folded position and a deployed position.
- 根据权利要求1所述的机臂组件,其特征在于,The arm assembly of claim 1 wherein:所述机臂包括与所述固定座转动连接的近端部,所述近端部设置有第一凹槽和第二凹槽;The arm includes a proximal end rotatably coupled to the mount, the proximal end being provided with a first recess and a second recess;所述弹性锁紧件包括与所述第一凹槽或第二凹槽卡合的压块和用于将所述压块压入所述第一凹槽或第二凹槽内的弹性元件;The elastic locking member includes a pressing block that engages with the first groove or the second groove and a resilient member for pressing the pressing piece into the first groove or the second groove;当所述机臂处于所述折叠位置时,所述压块卡合于所述第一凹槽;当所述机臂处于所述展开位置时,所述压块卡合于所述第二凹槽;当所述机臂处于所述折叠位置与所述展开位置之间时,所述弹性元件被压缩。The pressing block is engaged with the first groove when the arm is in the folded position; the pressing block is engaged with the second concave when the arm is in the deployed position a slot; the resilient member is compressed when the arm is between the folded position and the deployed position.
- 根据权利要求2所述的机臂组件,其特征在于,The arm assembly of claim 2, wherein所述第一凹槽或所述第二凹槽为圆弧槽,所述压块为圆弧形的压块。The first groove or the second groove is a circular arc groove, and the pressure block is a circular arc-shaped pressure piece.
- 根据权利要求1-3任一项所述的机臂组件,其特征在于,The arm assembly according to any one of claims 1 to 3, characterized in that所述固定座包括上壁、与所述上壁相对设置的下壁以及连接所述上壁和所述下壁的侧壁,所述上壁、所述下壁和所述侧壁围设形成一容置腔,所述机臂的所述近端部设置于所述容置腔内。The fixing base includes an upper wall, a lower wall opposite to the upper wall, and a side wall connecting the upper wall and the lower wall, and the upper wall, the lower wall and the side wall are circumferentially formed The accommodating cavity is disposed in the accommodating cavity.
- 根据权利要求5所述的机臂组件,其特征在于,The arm assembly of claim 5, wherein所述近端部设置有安装孔;The proximal end portion is provided with a mounting hole;所述机臂组件还包括穿设于所述安装孔并于所述固定座相连的转动连接件。The arm assembly further includes a rotating connector that is disposed through the mounting hole and connected to the fixing base.
- 根据权利要求5所述的机臂组件,其特征在于,所述转动连接件包括具有内螺纹孔的转轴和与所述内螺纹孔螺纹连接的螺钉,所述转轴穿设于所述安装孔。The arm assembly according to claim 5, wherein the rotary joint comprises a rotating shaft having an internally threaded bore and a screw threadedly coupled to the internally threaded bore, the rotary shaft passing through the mounting bore.
- 根据权利要求5所述的机臂组件,其特征在于,所述转动连接件为转轴,所述转轴的两端分别与所述固定座的上壁和下壁相连。The arm assembly according to claim 5, wherein the rotating connecting member is a rotating shaft, and both ends of the rotating shaft are respectively connected to upper and lower walls of the fixing base.
- 根据权利要求4-7中任一项所述的机臂组件,其特征在于,所述弹性锁紧件安装于所述侧壁。The arm assembly according to any one of claims 4 to 7, wherein the elastic locking member is mounted to the side wall.
- 根据权利要求4-8中任一项所述的机臂组件,其特征在于,A boom assembly according to any one of claims 4-8, wherein在所述机臂处于所述折叠位置时,所述机臂与所述固定座的侧壁平行;The arm is parallel to a side wall of the fixing seat when the arm is in the folded position;在所述机臂处于所述展开位置时,所述机臂与所述固定座的侧壁成预设夹角。When the arm is in the deployed position, the arm is at a predetermined angle with a sidewall of the fixing seat.
- 一种飞行器的机架,其特征在于,所述机架包括机身和与所述机身相连的如权利要求1-9中任一项所述的机臂组件。A frame for an aircraft, characterized in that the frame comprises a fuselage and the arm assembly of any one of claims 1-9 connected to the fuselage.
- 根据权利要求10所述的飞行器的机架,其特征在于,A frame for an aircraft according to claim 10, wherein所述机身的同一侧设置有两组所述机臂组件,在所述机架处于折叠状态时,位于所述机身同一侧的所述两组机臂组件的机臂相较于所述机身底部的高度不相同。The same side of the fuselage is provided with two sets of the arm assemblies, and when the rack is in a folded state, the arms of the two sets of arm assemblies on the same side of the fuselage are compared to the The height of the bottom of the fuselage is not the same.
- 一种飞行器,其特征在于,所述飞行器包括如权利要求10或11所述的机架和安装于所述机架内部的飞行控制模块。An aircraft characterized in that the aircraft comprises a frame as claimed in claim 10 or 11 and a flight control module mounted inside the frame.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201721008359.9 | 2017-08-10 | ||
CN201721008359.9U CN207141359U (en) | 2017-08-10 | 2017-08-10 | Horn component, frame and the unmanned vehicle of a kind of aircraft |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2019029387A1 true WO2019029387A1 (en) | 2019-02-14 |
Family
ID=61665496
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/CN2018/097520 WO2019029387A1 (en) | 2017-08-10 | 2018-07-27 | Aerial vehicle and arm assembly and frame thereof |
Country Status (2)
Country | Link |
---|---|
CN (1) | CN207141359U (en) |
WO (1) | WO2019029387A1 (en) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN207141359U (en) * | 2017-08-10 | 2018-03-27 | 深圳市道通智能航空技术有限公司 | Horn component, frame and the unmanned vehicle of a kind of aircraft |
CN113795424A (en) * | 2020-06-01 | 2021-12-14 | 深圳市大疆创新科技有限公司 | Arm subassembly and unmanned vehicles |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR101456035B1 (en) * | 2014-09-06 | 2014-11-04 | 최종필 | The rotor arm device of multi-rotor type drone |
CN205022844U (en) * | 2015-09-30 | 2016-02-10 | 湖南云顶智能科技有限公司 | Unmanned aerial vehicle horn folding mechanism and unmanned aerial vehicle |
CN205186525U (en) * | 2015-11-24 | 2016-04-27 | 深圳飞马机器人科技有限公司 | Many rotor unmanned aerial vehicle's horn auto -lock folding mechanism |
CN205633049U (en) * | 2016-04-08 | 2016-10-12 | 四川克瑞斯航空科技有限公司 | Collapsible many rotor unmanned aerial vehicle of horn |
CN206187327U (en) * | 2016-11-25 | 2017-05-24 | 广州亿航智能技术有限公司 | Foldable unmanned vehicles and horn thereof |
CN207060376U (en) * | 2017-07-24 | 2018-03-02 | 深圳市道通智能航空技术有限公司 | A kind of horn attachment structure and there is its unmanned plane |
CN207141359U (en) * | 2017-08-10 | 2018-03-27 | 深圳市道通智能航空技术有限公司 | Horn component, frame and the unmanned vehicle of a kind of aircraft |
-
2017
- 2017-08-10 CN CN201721008359.9U patent/CN207141359U/en active Active
-
2018
- 2018-07-27 WO PCT/CN2018/097520 patent/WO2019029387A1/en active Application Filing
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR101456035B1 (en) * | 2014-09-06 | 2014-11-04 | 최종필 | The rotor arm device of multi-rotor type drone |
CN205022844U (en) * | 2015-09-30 | 2016-02-10 | 湖南云顶智能科技有限公司 | Unmanned aerial vehicle horn folding mechanism and unmanned aerial vehicle |
CN205186525U (en) * | 2015-11-24 | 2016-04-27 | 深圳飞马机器人科技有限公司 | Many rotor unmanned aerial vehicle's horn auto -lock folding mechanism |
CN205633049U (en) * | 2016-04-08 | 2016-10-12 | 四川克瑞斯航空科技有限公司 | Collapsible many rotor unmanned aerial vehicle of horn |
CN206187327U (en) * | 2016-11-25 | 2017-05-24 | 广州亿航智能技术有限公司 | Foldable unmanned vehicles and horn thereof |
CN207060376U (en) * | 2017-07-24 | 2018-03-02 | 深圳市道通智能航空技术有限公司 | A kind of horn attachment structure and there is its unmanned plane |
CN207141359U (en) * | 2017-08-10 | 2018-03-27 | 深圳市道通智能航空技术有限公司 | Horn component, frame and the unmanned vehicle of a kind of aircraft |
Also Published As
Publication number | Publication date |
---|---|
CN207141359U (en) | 2018-03-27 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CN107000834B (en) | More rotor unmanned aircrafts | |
CN109733587B (en) | Coupling assembling, unmanned vehicles's horn and unmanned vehicles | |
CN109502006B (en) | Unmanned aerial vehicle frame, unmanned aerial vehicle and using method thereof | |
US11420734B2 (en) | Propeller, propeller kit, power assembly, power kit and unmanned aerial vehicle | |
US20200307826A1 (en) | Damping device, gimbal assembly having same, and unmanned aerial vehicle | |
US10717527B2 (en) | UAV arm mechanism and UAV | |
WO2018076470A1 (en) | Unmanned aerial vehicle | |
US20170291677A1 (en) | Folding heavy-lift unmanned aerial vehicle frame | |
WO2019029387A1 (en) | Aerial vehicle and arm assembly and frame thereof | |
CN106081057A (en) | A kind of stable multiaxis unmanned plane | |
CN108513555B (en) | Foldable rack, rack assembly and unmanned aerial vehicle | |
WO2019242225A1 (en) | Unmanned aerial vehicle, arm assembly and rotary shaft mechanism thereof | |
CN111099011A (en) | Aircraft | |
CN206502009U (en) | A kind of multiaxis unmanned plane of stabilization | |
CN204802065U (en) | Collapsible oar arm component and unmanned aerial vehicle | |
US20220227485A1 (en) | Unmanned aerial vehicle folding landing gear | |
CN214608062U (en) | Arm and unmanned aerial vehicle | |
CN205469768U (en) | Support arm turn mechanism suitable for large -scale many rotors | |
WO2020135448A1 (en) | Unmanned aerial vehicle | |
CN214165276U (en) | Coupling assembling, frame and unmanned aerial vehicle | |
WO2023035236A1 (en) | Frame for unmanned aerial vehicle, unmanned aerial vehicle, and kit | |
US11319046B2 (en) | Folding heavy-lift unmanned aerial vehicle frame | |
WO2020057115A1 (en) | Arm folding assembly and unmanned aerial vehicle | |
CN209441606U (en) | A kind of horn folded piece | |
CN210000572U (en) | unmanned aerial vehicle |
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: 18845260 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: 18845260 Country of ref document: EP Kind code of ref document: A1 |