WO2017107752A1 - 机臂可折放的多旋翼载人飞行器 - Google Patents

机臂可折放的多旋翼载人飞行器 Download PDF

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Publication number
WO2017107752A1
WO2017107752A1 PCT/CN2016/108362 CN2016108362W WO2017107752A1 WO 2017107752 A1 WO2017107752 A1 WO 2017107752A1 CN 2016108362 W CN2016108362 W CN 2016108362W WO 2017107752 A1 WO2017107752 A1 WO 2017107752A1
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WO
WIPO (PCT)
Prior art keywords
arm
mounting hole
fixing mechanism
fastener
arms
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PCT/CN2016/108362
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English (en)
French (fr)
Inventor
杜昊
胡华智
李智奕
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广州亿航智能技术有限公司
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Application filed by 广州亿航智能技术有限公司 filed Critical 广州亿航智能技术有限公司
Publication of WO2017107752A1 publication Critical patent/WO2017107752A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/08—Helicopters with two or more rotors
    • B64C27/10—Helicopters with two or more rotors arranged coaxially
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
    • 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
    • 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

  • the present application relates to the field of aircraft technology, and in particular to a multi-rotor manned aircraft with a foldable arm.
  • the present application aims to overcome the shortcomings of the prior art, and provides a multi-rotor manned aircraft with a simple structure and a foldable arm for convenient transportation and collection.
  • a multi-rotor manned aircraft with a movable arm comprising an aircraft body, a fixing mechanism, a connecting member and an arm, wherein the fixing mechanism is fixed on the aircraft body, and one end of the arm is hinged on the fixing mechanism,
  • the fixing mechanism is provided with a first mounting hole
  • the arm is provided with a second mounting hole.
  • one end of the connecting member is provided with a third mounting hole, and the first fastener passes through the first mounting hole and the third mounting hole at the same time, so that one end of the connecting member is connected with the fixing mechanism;
  • the other end of the connecting member is provided with a fourth mounting hole, and the second fastener passes through the second mounting hole and the fourth mounting hole at the same time, so that the other end of the connecting member is connected with the arm.
  • the fixing mechanism includes a first fixing member and a second fixing member, the first fixing member and the second fixing member are spaced apart from each other on the aircraft body, and the first fixing member and the second fixing member are fixed.
  • a rotating shaft is connected between the pieces, and one end of the arm is hinged on the rotating shaft.
  • the first mounting holes are two, and the two first mounting holes are respectively disposed on the first fixing member and the second fixing member.
  • one end of the arm is sleeved, the bottom of the sleeve is spaced apart from two ears, the second mounting holes are two, and the two second mountings The holes are respectively arranged on the two ear plates.
  • the first fastener is a pin, rivet or bolt.
  • the second fastener is a pin, rivet or bolt.
  • the third fastener is a pin, rivet or bolt.
  • the multi-rotor manned aircraft of the above-mentioned arm can be folded, and the arm is hinged with the fixing mechanism, which can change the angle between the arm and the fixing mechanism, and realize the switching of the folding state and the use state of the arm.
  • the first fastener and the second fastener are used to install the connecting member, so that the fixing mechanism and the arm maintain a first angle, thereby effectively reducing the occupied space; when the aircraft is used, the connecting member is removed and passed
  • the third fastener connects the fixing mechanism and the arm, so that the fixing mechanism and the arm maintain a second angle, the structure is simple, and the installation is convenient.
  • FIG. 1 is a first schematic view of a multi-rotor manned aircraft with a retractable arm according to an embodiment of the present invention in use;
  • FIG. 2 is a second schematic view of the multi-rotor manned aircraft with the arm retractable according to the embodiment of the present invention in use;
  • FIG. 3 is a first schematic view of the multi-rotor manned aircraft with the arm retractable in the folded state according to the embodiment of the present application;
  • FIG. 4 is a second schematic view of the multi-rotor manned aircraft with the arm that can be folded in the folded state according to the embodiment of the present application.
  • Fixing mechanism 2, connecting piece, 3, arm, 4, sleeve, 10, first fixing member, 10a, first mounting hole, 11, second fixing member, 12, rotating shaft, 40a, second mounting Hole, 100, aircraft body.
  • the multi-rotor manned aircraft that can be folded by the arm of the embodiment includes an aircraft body 100, a fixing mechanism 1, a connecting member 2 and an arm 3.
  • the fixing mechanism 1 is fixed at On the aircraft body 100, one end of the arm 3 is hinged to the fixing mechanism 1.
  • the fixing mechanism 1 is provided with a first mounting hole 10a, and the arm 3 is provided with a second mounting hole 40a. 3 is in a folded state, one end of the connecting member 2 is detachably connected to the fixing mechanism 1 by a first fastener, and the other end of the connecting member 2 is detachably connected to the arm 3 by a second fastener.
  • the fixing mechanism 1 and the arm 3 are maintained at a first angle; when the arm 3 is in the use state, the third fastener passes through the first mounting hole 10a and the second mounting hole 40a at the same time, so that the fixing mechanism 1 and the machine
  • the arm 3 is fixedly attached and maintained at a second angle.
  • the multi-rotor manned aircraft of the above-mentioned arm can be folded, and the arm 3 is hinged with the fixing mechanism 1, and the angle between the arm 3 and the fixing mechanism 1 can be changed, and the folding state and the use state of the arm 3 can be switched.
  • the connecting member 2 When transporting and storing the aircraft, the connecting member 2 is installed by the first fastener and the second fastener, so that the fixing mechanism 1 and the arm 3 maintain the first angle, thereby effectively reducing the occupied space; and removing the connecting member when the aircraft is used 2, and the fixing mechanism 1 and the arm 3 are connected by the third fastener, so that the fixing mechanism 1 and the arm 3 maintain the second angle, the structure is simple, and the installation is convenient.
  • one end of the connecting member 2 is provided with a third mounting hole, and the first fastener passes through the first mounting hole 10a and the third mounting hole at the same time, so that one end of the connecting member 2 is connected with the fixing mechanism 1;
  • the other end of the connecting member 2 is provided with a fourth mounting hole, and the second fastener passes through the second mounting hole 40a and the fourth mounting hole at the same time, so that the other end of the connecting member 2 is connected with the arm 3 without additional Open the hole to reduce manufacturing costs.
  • the fixing mechanism 1 includes a first fixing member 10 and a second fixing member 11.
  • the first fixing member 10 and the second fixing member 11 are spaced apart from each other on the aircraft body 100.
  • a rotating shaft 12 is connected between the piece 10 and the second fixing member 11, and one end of the arm 3 is hinged on the rotating shaft 12.
  • the arm 3 is hinged on the fixing mechanism 1 by a shaft pin, and the work is reliable and the disassembly is convenient.
  • the first mounting holes 10a are two, and the two first mounting holes 10a are respectively disposed on the first fixing member 10 and the second fixing member 11, the first fasteners.
  • One end of the arm 3 is sleeved with a sleeve 4, and the bottom of the sleeve 4 is spaced apart from two ears.
  • the second mounting holes 40a are two, and the two second mounting holes 40a are respectively Correspondingly disposed on two ear plates, the second fastener is a pin shaft.
  • one end of the connecting member 2 is fixed to the fixing mechanism 1 by a pin shaft, and the other end of the connecting member 2 is fixed to the arm 3 by a pin shaft for easy disassembly.
  • the third fastener is a rivet. When the aircraft is used, the connecting member 2 is removed, and the fixing mechanism 1 and the arm 3 are connected by a rivet, and the connection is reliable.
  • the first fastener may use a fastener such as a rivet or a bolt
  • the second fastener may use a fastener such as a rivet or a bolt
  • the third fastening may be used, and the selected fasteners are based on actual conditions.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Remote Sensing (AREA)
  • Connection Of Plates (AREA)
  • Pivots And Pivotal Connections (AREA)

Abstract

一种机臂可折放的多旋翼载人飞行器，包括飞行器本体（100）、固定机构（1）、连接件（2）及机臂（3），固定机构（1）固定在飞行器本体（100）上，机臂（3）的一端铰接在固定机构（1）上，固定机构（1）上设有第一安装孔（10a），机臂（3）上设有第二安装孔（40a），当机臂（3）处于折放状态时，连接件（2）的一端通过第一紧固件可拆卸连接在固定机构（1）上，连接件（2）的另一端通过第二紧固件可拆卸连接在机臂（3）上，使得固定机构（1）与机臂（3）保持第一角度；当机臂处于使用状态时，第三紧固件同时穿过第一安装孔（10a）与第二安装孔（40a），使得固定机构（1）与机臂（3）固定连接并保持第二角度。该机臂可折放的多旋翼载人飞行器能改变机臂与固定机构之间的角度，实现机臂的折放状态与使用状态的切换，方便进行运输和收藏。

Description

机臂可折放的多旋翼载人飞行器 技术领域
本申请涉及飞行器技术领域，特别涉及一种机臂可折放的多旋翼载人飞行器。
背景技术
近年来飞行器技术飞速发展，各种类型的飞行器不断涌现。其中，小型载人飞行器(如个人飞行器)因其灵巧轻便、操作简单的特点，受到了人们的追捧。这类飞行器的机臂通常固定在机身上，采用的固定方式往往是焊接。这种连接方式导致飞行器占用空间大，不便于运输和收藏，给使用者带来很大的麻烦。
发明内容
基于此，本申请在于克服现有技术的缺陷，提供一种结构简单的机臂可折放的多旋翼载人飞行器，方便进行运输和收藏。
其技术方案如下：
一种机臂可折放的多旋翼载人飞行器，包括飞行器本体、固定机构、连接件及机臂，所述固定机构固定在飞行器本体上，所述机臂的一端铰接在固定机构上，所述固定机构上设有第一安装孔，所述机臂上设有第二安装孔，当机臂处于折放状态时，所述连接件的一端通过第一紧固件可拆卸连接在固定机构上，所述连接件的另一端通过第二紧固件可拆卸连接在机臂上，使得固定机构与机臂保持第一角度；当机臂处于使用状态时，第三紧固件同时穿过第一安装孔与第二安装孔，使得固定机构与机臂固定连接并保持第二角度。
在其中一个实施例中，所述连接件的一端设有第三安装孔，所述第一紧固件同时穿过第一安装孔与第三安装孔，使得连接件的一端与固定机构连接；所述连接件的另一端设有第四安装孔，所述第二紧固件同时穿过第二安装孔与第四安装孔，使得连接件的另一端与机臂连接。
在其中一个实施例中，所述固定机构包括第一固定件及第二固定件，所述第一固定件与第二固定件间隔设置在飞行器本体上，所述第一固定件与第二固定件之间连接有转轴，所述机臂的一端铰接在转轴上。
在其中一个实施例中，所述第一安装孔为两个，两个所述第一安装孔分别对应设置在第一固定件及第二固定件上。
在其中一个实施例中，所述机臂的一端套设有套筒，所述套筒的底部间隔设有两个耳板，所述第二安装孔为两个，两个所述第二安装孔分别对应设置在两个耳板上。
在其中一个实施例中，所述第一紧固件为销轴、铆钉或螺栓。
在其中一个实施例中，所述第二紧固件为销轴、铆钉或螺栓。
在其中一个实施例中，所述第三紧固件为销轴、铆钉或螺栓。
下面对前述技术方案的优点或原理进行说明：
上述机臂可折放的多旋翼载人飞行器，机臂与固定机构铰接，能改变机臂与固定机构之间的角度，实现机臂的折放状态与使用状态的切换。在运输和收藏飞行器时，通过第一紧固件、第二紧固件安装连接件，使得固定机构与机臂保持第一角度，有效减少占用空间；在使用飞行器时拆下连接件，并通过第三紧固件连接固定机构与机臂，使得固定机构与机臂保持第二角度，结构简单，安装方便。
附图说明
图1为本申请实施例所述的机臂可折放的多旋翼载人飞行器处于使用状态时的示意图一；
图2为本申请实施例所述的机臂可折放的多旋翼载人飞行器处于使用状态时的示意图二；
图3为本申请实施例所述的机臂可折放的多旋翼载人飞行器处于折放状态时的示意图一；
图4为本申请实施例所述的机臂可折放的多旋翼载人飞行器处于折放状态时的示意图二。
附图标记说明：
1、固定机构，2、连接件，3、机臂，4、套筒，10、第一固定件，10a、第一安装孔，11、第二固定件，12、转轴，40a、第二安装孔，100、飞行器本体。
具体实施方式
下面对本申请的实施例进行详细说明：
如图1-4所示，本实施例所述的机臂可折放的多旋翼载人飞行器，包括飞行器本体100、固定机构1、连接件2及机臂3，所述固定机构1固定在飞行器本体100上，所述机臂3的一端铰接在固定机构1上，所述固定机构1上设有第一安装孔10a，所述机臂3上设有第二安装孔40a，当机臂3处于折放状态时，所述连接件2的一端通过第一紧固件可拆卸连接在固定机构1上，所述连接件2的另一端通过第二紧固件可拆卸连接在机臂3上，使得固定机构1与机臂3保持第一角度；当机臂3处于使用状态时，第三紧固件同时穿过第一安装孔10a与第二安装孔40a，使得固定机构1与机臂3固定连接并保持第二角度。上述机臂可折放的多旋翼载人飞行器，机臂3与固定机构1铰接，能改变机臂3与固定机构1之间的角度，实现机臂3的折放状态与使用状态的切换。在运输和收藏飞行器时，通过第一紧固件、第二紧固件安装连接件2，使得固定机构1与机臂3保持第一角度，有效减少占用空间；在使用飞行器时拆下连接件2，并通过第三紧固件连接固定机构1与机臂3，使得固定机构1与机臂3保持第二角度，结构简单，安装方便。
其中，所述连接件2的一端设有第三安装孔，所述第一紧固件同时穿过第一安装孔10a与第三安装孔，使得连接件2的一端与固定机构1连接；所述连接件2的另一端设有第四安装孔，所述第二紧固件同时穿过第二安装孔40a与第四安装孔，使得连接件2的另一端与机臂3连接，无需额外开孔，降低制造成本。
如图4所示，所述固定机构1包括第一固定件10及第二固定件11，所述第一固定件10与第二固定件11间隔设置在飞行器本体100上，所述第一固定件10与第二固定件11之间连接有转轴12，所述机臂3的一端铰接在转轴12上。 机臂3通过轴销铰接在固定机构1上，工作可靠，拆卸方便。
在本实施例中，所述第一安装孔10a为两个，两个所述第一安装孔10a分别对应设置在第一固定件10及第二固定件11上，所述第一紧固件为销轴。所述机臂3的一端套设有套筒4，所述套筒4的底部间隔设有两个耳板，所述第二安装孔40a为两个，两个所述第二安装孔40a分别对应设置在两个耳板上，所述第二紧固件为销轴。在运输和收藏飞行器时，连接件2的一端通过销轴固定在固定机构1上，连接件2的另一端通过销轴固定在机臂3上，便于拆卸。所述第三紧固件为铆钉，在使用飞行器时拆下连接件2，并通过铆钉连接固定机构1与机臂3，连接可靠。
可以理解的，在其它实施例中，所述第一紧固件可以采用铆钉或螺栓等紧固件，所述第二紧固件可以采用铆钉或螺栓等紧固件，所述第三紧固件可以采用销轴或螺栓等紧固件，选取的紧固件根据实际情况而定。
以上所述实施例的各技术特征可以进行任意的组合，为使描述简洁，未对上述实施例中的各个技术特征所有可能的组合都进行描述，然而，只要这些技术特征的组合不存在矛盾，都应当认为是本说明书记载的范围。
以上所述实施例仅表达了本申请的几种实施方式，其描述较为具体和详细，但并不能因此而理解为对专利申请范围的限制。应当指出的是，对于本领域的普通技术人员来说，在不脱离本申请构思的前提下，还可以做出若干变形和改进，这些都属于本申请的保护范围。因此，本专利申请的保护范围应以所附权利要求为准。

Claims (8)

  1. 一种机臂可折放的多旋翼载人飞行器，其特征在于，包括飞行器本体、固定机构、连接件及机臂，所述固定机构固定在飞行器本体上，所述机臂的一端铰接在固定机构上，所述固定机构上设有第一安装孔，所述机臂上设有第二安装孔，当机臂处于折放状态时，所述连接件的一端通过第一紧固件可拆卸连接在固定机构上，所述连接件的另一端通过第二紧固件可拆卸连接在机臂上，使得固定机构与机臂保持第一角度；当机臂处于使用状态时，第三紧固件同时穿过第一安装孔与第二安装孔，使得固定机构与机臂固定连接并保持第二角度。
  2. 根据权利要求1所述的机臂可折放的多旋翼载人飞行器，其特征在于，所述连接件的一端设有第三安装孔，所述第一紧固件同时穿过第一安装孔与第三安装孔，使得连接件的一端与固定机构连接；所述连接件的另一端设有第四安装孔，所述第二紧固件同时穿过第二安装孔与第四安装孔，使得连接件的另一端与机臂连接。
  3. 根据权利要求1所述的机臂可折放的多旋翼载人飞行器，其特征在于，所述固定机构包括第一固定件及第二固定件，所述第一固定件与第二固定件间隔设置在飞行器本体上，所述第一固定件与第二固定件之间连接有转轴，所述机臂的一端铰接在转轴上。
  4. 根据权利要求3所述的机臂可折放的多旋翼载人飞行器，其特征在于，所述第一安装孔为两个，两个所述第一安装孔分别对应设置在第一固定件及第二固定件上。
  5. 根据权利要求1所述的机臂可折放的多旋翼载人飞行器，其特征在于，所述机臂的一端套设有套筒，所述套筒的底部间隔设有两个耳板，所述第二安装孔为两个，两个所述第二安装孔分别对应设置在两个耳板上。
  6. 根据权利要求1-5任一项所述的机臂可折放的多旋翼载人飞行器，其特征在于，所述第一紧固件为销轴、铆钉或螺栓。
  7. 根据权利要求1-5任一项所述的机臂可折放的多旋翼载人飞行器，其特征在于，所述第二紧固件为销轴、铆钉或螺栓。
  8. 根据权利要求1-5任一项所述的机臂可折放的多旋翼载人飞行器，其特征在于，所述第三紧固件为销轴、铆钉或螺栓。
PCT/CN2016/108362 2015-12-25 2016-12-02 机臂可折放的多旋翼载人飞行器 WO2017107752A1 (zh)

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