WO2021189162A1 - 一种无人机机架 - Google Patents

一种无人机机架 Download PDF

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Publication number
WO2021189162A1
WO2021189162A1 PCT/CN2020/080539 CN2020080539W WO2021189162A1 WO 2021189162 A1 WO2021189162 A1 WO 2021189162A1 CN 2020080539 W CN2020080539 W CN 2020080539W WO 2021189162 A1 WO2021189162 A1 WO 2021189162A1
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WO
WIPO (PCT)
Prior art keywords
sliding block
spring
frame body
rod
buffer
Prior art date
Application number
PCT/CN2020/080539
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English (en)
French (fr)
Inventor
杨哲
沈亭
Original Assignee
南京唐壹信息科技有限公司
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 南京唐壹信息科技有限公司 filed Critical 南京唐壹信息科技有限公司
Priority to PCT/CN2020/080539 priority Critical patent/WO2021189162A1/zh
Publication of WO2021189162A1 publication Critical patent/WO2021189162A1/zh

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/58—Arrangements or adaptations of shock-absorbers or springs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/58—Arrangements or adaptations of shock-absorbers or springs
    • B64C25/62—Spring shock-absorbers; Springs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/58—Arrangements or adaptations of shock-absorbers or springs
    • B64C25/62—Spring shock-absorbers; Springs
    • B64C25/64—Spring shock-absorbers; Springs using rubber or like elements

Definitions

  • the invention relates to a drone frame.
  • UAVs on the market will be equipped with a buffer structure.
  • the existing UAV buffer is generally equipped with a rubber pad on the drone frame. The rubber pad is wrapped on the landing gear of the unmanned home.
  • the buffer structure has a poor buffering effect. The use is not ideal.
  • the present invention provides an unmanned aerial vehicle frame in order to solve the above-mentioned problems in the prior art.
  • a drone frame including a frame body, a buffer rod, a guide rod, a first spring, a second spring, a first sliding block, a second sliding block, a mounting block and a connection Rods, a number of guide rods are fixed on the upper and lower end faces of the frame body, and the guide rods on the upper end face of the frame body and the guide rods on the lower end face of the frame body are arranged in the form of spokes;
  • the first spring, the second spring, the first sliding block and the second sliding block are slidably connected, the mounting block is fixedly connected to the guide rod, and the first sliding block and the second sliding block are placed on both sides of the mounting block.
  • Both ends of the first slider and the second slider are provided with a first spring and a second spring, and the first spring and the second spring correspond to the first slider and the second slider; the buffer rod
  • the top ends of the two connecting rods are all hinged on the buffer rod, and the bottom ends of the two connecting rods are correspondingly hinged on the first sliding block and the second sliding block.
  • the end of the guide rod is provided with a limiting protrusion, and the first spring abuts on the limiting protrusion.
  • the buffer bar is inclined outwards on the frame body, and the inclination angle is 20-35°.
  • a rubber sleeve is sleeved on the buffer rod.
  • the frame body is made of aluminum.
  • At least four guide rods are provided on each end surface of the frame body.
  • the invention integrates the landing gear and the buffer of the drone into one body, ensuring a good buffer effect while not occupying space, with simple structure and reasonable design.
  • the weight of the drone is pressed on the buffer rod Above, the buffer rod 2 compresses the spring to play a buffer role.
  • the spring rebounds, which can give the UAV a force to facilitate the UAV to take off.
  • Figure 1 is a front view of the present invention.
  • Figure 2 is a top view of the present invention.
  • Fig. 3 is a diagram of the installation structure of the buffer rod in the present invention.
  • an unmanned aerial vehicle frame of the present invention includes a frame body 1, a buffer rod 2, a guide rod 3, a first spring 4, a second spring 5, a first sliding block 6, and a second sliding block.
  • a number of guide rods 3 are fixed on the upper and lower end surfaces of the frame body 1, and the guide rods 3 on the upper end of the frame body 1 and the guide rods 3 on the lower end of the frame body 1 are both arranged in a spoke shape.
  • the first spring 4, the second spring 5, the first slider 6 and the second slider 7 are slidably connected to each guide rod 3, and the mounting block 8 is fixedly connected to the guide rod 3, wherein the first slider 6
  • the second and second sliding blocks 7 are placed on both sides of the mounting block 8.
  • a first spring 4 and a second spring 5 are provided at both ends of the first sliding block 6 and both ends of the second sliding block 7. The first spring 4 and the second spring 5 abut on the first slider 6 and the second slider 7 correspondingly.
  • the buffer rod 2 is obliquely and fixedly connected to the mounting block 8. All the buffer rods 2 on the upper end surface of the frame body 1 and all the buffer rods 2 on the lower end surface form an outwardly expanding landing gear structure.
  • Two connecting rods 9 are hinged on each buffer rod 2, the top ends of the two connecting rods 9 are hinged to the buffer rod 2, and the bottom ends of the two connecting rods 9 are correspondingly hinged to the first slider 6 and the second slider 7 on.
  • a limit protrusion 31 is provided at the end of the guide rod 3, and the first spring 4 abuts on the limit protrusion 31.
  • the buffer bar 2 in the present invention is inclined outward on the frame body 1, and the inclination angle is 20-35°.
  • a rubber sleeve is sleeved on the buffer rod 2.
  • the rubber sleeve can better protect the buffer rod, and on the other hand, the rubber sleeve can also play a buffer role.
  • the frame body 1 in the present invention is made of aluminum and has high strength.
  • At least four guide rods 3 are provided on each end surface of the frame body 1.
  • the invention integrates the landing gear and the buffer of the drone into one body, ensuring a good buffer effect while not occupying space.
  • the structure is simple and the design is reasonable.
  • the weight of the drone is pressed on the buffer rod.
  • the buffer rod 2 compresses the spring to play a buffer role.
  • the spring rebounds, which can give the UAV a force to facilitate the UAV to take off.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Vibration Dampers (AREA)

Abstract

一种无人机机架，在机架本体（1）的上端面和下端面均固定若干根导向杆（3），且机架本体（1）上端面的导向杆（3）与机架本体（1）下端面的导向杆（3）均成轮辐状布置；在每根导向杆（3）上均滑动穿接第一弹簧（4）、第二弹簧（5）、第一滑块（6）、第二滑块（7）和安装块（8），第一滑块（6）和第二滑块（7）置于安装块（8）的两侧，在第一滑块（6）的两端和第二滑块（7）的两端均设有第一弹簧（4）和第二弹簧（5），且第一弹簧（4）和第二弹簧（5）对应抵触在第一滑块（6）和第二滑块（7）上；缓冲杆（2）倾斜固定连接在安装块（8）上，两根连接杆（9）的顶端均铰接在缓冲杆（2）上，两连接杆（9）的底端对应铰接在第一滑块（6）和第二滑块（7）上。

Description

一种无人机机架 技术领域：
本发明涉及一种无人机机架。
背景技术：
现有的无人机在落地时由于受到惯性的作用会产生强烈的震动，长时间如此会造成无人机零件受损变形或零件松动脱落。目前市面上的无人机会配备缓冲结构，现有的无人机缓冲普遍是在无人机机架上设置橡胶垫，橡胶垫包裹在无人家的起落架上，该中缓冲结构缓冲效果差，使用不理想。
发明内容：
本发明是为了解决上述现有技术存在的问题而提供一种无人机机架。
本发明所采用的技术方案有：一种无人机机架，包括机架本体、缓冲杆、导向杆、第一弹簧、第二弹簧、第一滑块、第二滑块、安装块和连接杆，在机架本体的上端面和下端面均固定若干根导向杆，且机架本体上端面的导向杆与机架本体下端面的导向杆均成轮辐状布置；在每根导向杆上均滑动穿接第一弹簧、第二弹簧、第一滑块和第二滑块，安装块固定连接在导向杆上，所述第一滑块和第二滑块置于安装块的两侧，在第一滑块的两端和第二滑块的两端均设有第一弹簧和第二弹簧，且第一弹簧和第二弹簧对应抵触在第一滑块和第二滑块上；缓冲杆倾斜固定连接在安装块上，两根连接杆的顶端均铰接在缓冲杆上，两连接杆的底端对应铰接在第一滑块和第二滑块上。
进一步地，所述导向杆的末端设有限位凸起，第一弹簧抵触在限位凸起上。
进一步地，所述缓冲杆在机架本体上向外倾斜，且倾斜的角度为20-35°。
进一步地，所述缓冲杆上套设有橡胶套。
进一步地，所述机架本体采用铝制成。
进一步地，所述机架本体每个端面上均至少设有四根导向杆。
本发明具有如下有益效果：
本发明将无人机的起落架与缓冲做成一体，在不占用空间的同时，保证好的缓冲效果，结构简单，设计合理，在无人机下落时，无人机的自重压在缓冲杆上，缓冲杆2压缩弹簧起到缓冲作用。在起飞时，弹簧回弹，可以给无人机一个作用力，方便无人机起 飞。
附图说明：
图1为本发明主视图。
图2为本发明俯视图。
图3为本发明中缓冲杆的安装结构图。
具体实施方式：
下面结合附图对本发明作进一步的说明。
如图1至图3，本发明一种无人机机架，包括机架本体1、缓冲杆2、导向杆3、第一弹簧4、第二弹簧5、第一滑块6、第二滑块7、安装块8和连接杆9。
在机架本体1的上端面和下端面均固定若干根导向杆3，且机架本体1上端面的导向杆3与机架本体1下端面的导向杆3均成轮辐状布置。在每根导向杆3上均滑动穿接第一弹簧4、第二弹簧5、第一滑块6和第二滑块7，安装块8固定连接在导向杆3上，其中第一滑块6和第二滑块7置于安装块8的两侧，在第一滑块6的两端和第二滑块7的两端均设有第一弹簧4和第二弹簧5。第一弹簧4和第二弹簧5对应抵触在第一滑块6和第二滑块7上。
缓冲杆2倾斜固定连接在安装块8上，机架本体1上端面所有的缓冲杆2和下端面所有的缓冲杆2组成向外扩张的起落架结构。在每根缓冲杆2上均铰接两根连接杆9，两根连接杆9的顶端均铰接在缓冲杆2上，两连接杆9的底端对应铰接在第一滑块6和第二滑块7上。
为便于对导向杆3上安装部件的进行轴向限位，在导向杆3的末端设有限位凸起31，第一弹簧4抵触在限位凸起31上。
本发明中的缓冲杆2在机架本体1上向外倾斜，且倾斜的角度为20-35°。
为避免缓冲杆2在降落时与地面刚性接触，在缓冲杆2上套设有橡胶套。橡胶套一方面可以更好地保护缓冲杆，另一方面，橡胶套也可以起到缓冲的作用。
本发明中的机架本体1采用铝制成，强度高。
为保证结构的稳定性，在机架本体1每个端面上均至少设有四根导向杆3。
本发明将无人机的起落架与缓冲做成一体，在不占用空间的同时，保证好的缓冲效果，结构简单，设计合理，在无人机下落时，无人机的自重压在缓冲杆上，缓冲杆2压 缩弹簧起到缓冲作用。在起飞时，弹簧回弹，可以给无人机一个作用力，方便无人机起飞。
以上所述仅是本发明的优选实施方式，应当指出，对于本技术领域的普通技术人员来说，在不脱离本发明原理的前提下还可以作出若干改进，这些改进也应视为本发明的保护范围。

Claims (6)

  1. 一种无人机机架，其特征在于：包括机架本体(1)、缓冲杆(2)、导向杆(3)、第一弹簧(4)、第二弹簧(5)、第一滑块(6)、第二滑块(7)、安装块(8)和连接杆(9)，在机架本体(1)的上端面和下端面均固定若干根导向杆(3)，且机架本体(1)上端面的导向杆(3)与机架本体(1)下端面的导向杆(3)均成轮辐状布置；在每根导向杆(3)上均滑动穿接第一弹簧(4)、第二弹簧(5)、第一滑块(6)和第二滑块(7)，安装块(8)固定连接在导向杆(3)上，所述第一滑块(6)和第二滑块(7)置于安装块(8)的两侧，在第一滑块(6)的两端和第二滑块(7)的两端均设有第一弹簧(4)和第二弹簧(5)，且第一弹簧(4)和第二弹簧(5)对应抵触在第一滑块(6)和第二滑块(7)上；缓冲杆(2)倾斜固定连接在安装块(8)上，两根连接杆(9)的顶端均铰接在缓冲杆(2)上，两连接杆(9)的底端对应铰接在第一滑块(6)和第二滑块(7)上。
  2. 如权利要求1所述的无人机机架，其特征在于：所述导向杆(3)的末端设有限位凸起(31)，第一弹簧(4)抵触在限位凸起(31)上。
  3. 如权利要求1所述的无人机机架，其特征在于：所述缓冲杆(2)在机架本体(1)上向外倾斜，且倾斜的角度为20-35°。
  4. 如权利要求1所述的无人机机架，其特征在于：所述缓冲杆(2)上套设有橡胶套。
  5. 如权利要求1所述的无人机机架，其特征在于：所述机架本体(1)采用铝制成。
  6. 如权利要求1所述的无人机机架，其特征在于：所述机架本体(1)每个端面上均至少设有四根导向杆(3)。
PCT/CN2020/080539 2020-03-22 2020-03-22 一种无人机机架 WO2021189162A1 (zh)

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB190930533A (en) * 1909-12-31 1910-11-17 Robert Blackburn Improvements in or in connection with Landing Devices for Aerial Machines.
CN107128481A (zh) * 2017-06-07 2017-09-05 西北工业大学 一种滚轮式液压阻尼无人机防摔起落架
CN206537493U (zh) * 2017-02-17 2017-10-03 内蒙古助农航空科技有限公司 一种无人机支腿
CN108357667A (zh) * 2018-01-22 2018-08-03 江苏理工学院 用于旋翼式无人机的缓冲型起落架
CN208931632U (zh) * 2018-08-03 2019-06-04 天津黎明时代信息技术有限公司 一种无人机用减震起落架

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB190930533A (en) * 1909-12-31 1910-11-17 Robert Blackburn Improvements in or in connection with Landing Devices for Aerial Machines.
CN206537493U (zh) * 2017-02-17 2017-10-03 内蒙古助农航空科技有限公司 一种无人机支腿
CN107128481A (zh) * 2017-06-07 2017-09-05 西北工业大学 一种滚轮式液压阻尼无人机防摔起落架
CN108357667A (zh) * 2018-01-22 2018-08-03 江苏理工学院 用于旋翼式无人机的缓冲型起落架
CN208931632U (zh) * 2018-08-03 2019-06-04 天津黎明时代信息技术有限公司 一种无人机用减震起落架

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