WO2019205460A1

WO2019205460A1 - Landing gear structure and unmanned aerial vehicle

Info

Publication number: WO2019205460A1
Application number: PCT/CN2018/106178
Authority: WO
Inventors: 王坤殿; 于建方; 张圣鑫; 陈旭东
Original assignee: 深圳市大疆创新科技有限公司
Priority date: 2018-04-24
Filing date: 2018-09-18
Publication date: 2019-10-31
Also published as: CN110896627A; CN208181404U

Abstract

Disclosed is a landing gear structure and an unmanned aerial vehicle. The landing gear structure (100) comprises a landing gear (10) and a quick-release assembly (20). The landing gear (10) comprises a main body portion (14) and an insertion connection portion (11) disposed on the main body portion (14). The quick-release assembly (20) comprises a first mounting portion (21) connected to an external main body structure, and a second mounting portion (22) connected to the first mounting portion (21). The second mounting portion (22) is provided with a slot (23) fitted with the insertion connection portion (11), and fixing members (24). The insertion connection portion (11) is inserted in the slot (23) and is fixed to the second mounting portion (22) by means of the fixing members (24). The landing gear (10) is inserted in the slot of the quick-release assembly by means of the insertion connection portion, is connected to the quick-release assembly by means of the fixing members, and is connected to the external main body structure by means of the first mounting portion of the quick-release assembly, and thus, the landing gear (10) is mounted on the external main body structure. The landing gear structure is simple and highly reliable, and can be easily mounted and dismounted.

Description

Landing gear structure and drone

Technical field

Embodiments of the present invention relate to the field of drone technology, and in particular, to a landing gear structure and a drone.

Background technique

As an important mechanism on the UAV equipment, the landing gear must be adapted to the overall design of the UAV, while also meeting the requirements of safety and reliability.

At present, the landing gear of an ordinary drone usually has two problems, one is the sturdy and durable structure, and the other is the lightweight structure. Some landing gears strengthen the structure but also add weight. Some landing gears reduce the weight but also weaken the structure, often losing sight of it. The existing quick release structure is often complicated, and further increases the weight and also reduces the reliability of the mechanism. Or some landing gears do not have a quick release structure at all, which brings a lot of inconvenience to the packaging transport.

Summary of the invention

Embodiments of the present invention provide a landing gear structure and a drone that are structurally reliable and can be quickly disassembled.

According to a first aspect of the embodiments of the present invention, a landing gear structure is provided, comprising: a landing gear and a quick release assembly;

The landing gear includes a main body portion and a plug portion provided at the main body portion, the quick release assembly including a first mounting portion for connecting with the outer main body structure and a second mounting connected to the first mounting portion The second mounting portion is provided with a slot and a fixing member that cooperate with the plug portion;

The insertion portion is inserted into the slot and fixed to the second mounting portion by the fixing member.

Further, the first mounting portion includes a socket portion that is sleeved on the outer body structure, and the outer side wall of the socket portion is connected to the second mounting portion.

Further, the second mounting portion includes two limiting portions and a connecting portion between the two limiting portions; the limiting portion is provided with the fixing member, and the connecting portion is opened Said slot.

Further, the two limiting portions are spaced apart from the connecting portion.

Further, a spacing distance between the two limiting portions is equal to a width of the insertion portion.

Further, the side walls of the two limiting portions are respectively provided with connecting holes, the connecting holes of the two limiting portions are coaxially disposed, and the two connecting holes are respectively provided with the Fastener.

Further, the fixing member is a ball plunger.

Further, the insertion portion is symmetrically disposed with the arcuate recesses adjacent to the two end portions of the two limiting portions, and cooperates with the fixing member.

Further, a side portion of the connecting portion is provided with a reinforcing wing connected to the first mounting portion.

Further, the landing gear is a swept-back landing gear.

Further, the main body portion is provided with a plurality of hollow portions along its length direction.

According to a second aspect of the embodiments of the present invention, there is provided a drone, comprising: a fuselage, an arm disposed on the fuselage, and a landing gear structure of any of the above embodiments, the quick release of the landing gear structure A first mounting portion of the assembly is coupled to the arm.

In the landing gear structure of the embodiment of the present invention, the landing gear is inserted into the slot of the second mounting portion of the quick release assembly through the plug portion, and is fixedly connected to the second mounting portion through the fixing member, thereby being connected with the quick release component, and then The first mounting portion of the quick release assembly is coupled to the outer body structure to mount the landing gear to the outer body structure. The structure is simple, reliable, and easy to disassemble.

DRAWINGS

1 is a schematic structural view of a landing gear structure according to an embodiment of the present invention.

2 is an exploded perspective view showing a structure of a landing gear according to an embodiment of the present invention.

3 is a perspective exploded view of a landing gear structure according to an embodiment of the invention.

4 is a perspective view of a drone according to an embodiment of the invention.

Figure 5 is a side elevational view of a drone according to an embodiment of the present invention.

Figure 6 is a front elevational view of a drone according to an embodiment of the present invention.

FIG. 7 is an enlarged schematic view showing a hatch cover and a body of a drone according to an embodiment of the present invention.

detailed description

Exemplary embodiments will be described in detail herein, examples of which are illustrated in the accompanying drawings. The following description refers to the same or similar elements in the different figures unless otherwise indicated. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the embodiments of the invention. Instead, they are merely examples of devices and methods consistent with aspects of the embodiments of the invention as detailed in the appended claims.

The terms used in the embodiments of the present invention are for the purpose of describing the specific embodiments, and are not intended to limit the embodiments of the present invention. The singular forms "a", "the" and "the" It should also be understood that the term "and/or" as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items.

It should be understood that the terms "first", "second", and <RTIgt; </ RTI> <RTIgt; </ RTI> <RTIgt; </ RTI> <RTIgt; Similarly, the words "a" or "an" and the like do not denote a quantity limitation, but mean that there is at least one. Unless otherwise indicated, the terms "front", "rear", "lower" and/or "upper" are used for convenience of description and are not limited to one location or one spatial orientation. The word "comprising" or "comprises" or "comprises" or "an" or "an" Or an object. The words "connected" or "connected" and the like are not limited to physical or mechanical connections, and may include electrical connections, whether direct or indirect.

Embodiments of the present invention provide a landing gear structure and a drone that are structurally reliable and can be quickly disassembled. The landing gear structure and the drone of the embodiment of the present invention will be described in detail below with reference to the accompanying drawings. The features of the embodiments and embodiments described below may be combined with each other without conflict.

As shown in FIG. 1 to FIG. 3, an embodiment of the present invention provides a landing gear structure 100 for mounting on an external body structure. In this embodiment, the external body structure may be an arm of a drone. The landing gear structure 100 includes a landing gear 10 and a quick release assembly 20 that is removably coupled to the quick release assembly 20.

Wherein the landing gear 10 includes a main body portion 14 and a plug portion 11 provided on the main body portion 14, the quick release assembly 20 includes a first mounting portion 21 for connecting with an external main body structure, and the first portion A second mounting portion 22 to which the mounting portion 21 is coupled, the second mounting portion 22 is provided with a slot 23 and a fixing member 24 that cooperate with the plug portion 11. The insertion portion 11 of the landing gear 10 is inserted into the slot 23 of the second mounting portion 22 of the quick release assembly 20 and is fixed to the second mounting portion 22 by the fixing member 24.

As can be seen from the above embodiment, the landing gear structure 100 of the embodiment of the present invention, the landing gear 10 is inserted into the slot 23 of the second mounting portion 22 of the quick release assembly 20 through the plug portion 11, and then passed through the fixing member 24 and the The second mounting portion 22 is fixedly coupled to the quick release assembly 20 and then coupled to the outer body structure by the first mounting portion 21 of the quick release assembly 20 to thereby mount the landing gear 10 to the outer body structure. When the landing gear 10 needs to be disassembled, the insertion portion 11 of the landing gear 10 is pulled out from the slot 23 of the second mounting portion 22 of the quick release assembly 20, and the decomposition of the landing gear 10 and the external main body structure is completed. The structure is simple, reliable, and easy to disassemble.

In an optional embodiment, the first mounting portion 21 of the quick release assembly 20 includes a socket portion 212 that is sleeved on the outer body structure, and the outer sidewall of the socket portion 212 is connected to the first portion. Second mounting portion 22. In this embodiment, the first mounting portion 21 is a sleeve member, and the side wall of the socket portion 212 is provided with a slit portion 213, so that the sleeve portion 212 has a certain amount of expansion and contraction, and is more convenient to be sleeved in the outer body structure. on.

In this embodiment, the outer body structure is an arm of the drone, and the arm is provided with a plurality of hole positions, and the outer side wall of the sleeve portion 212 may further be provided with a mounting hole 214 matching the hole position ( In the figure, the two mounting holes 214 are taken as an example. After the socket portion 212 is sleeved on the arm, the socket portion 212 is adjusted to a proper position, and can be worn by a fastener 215 (for example, a screw). In the hole position and the mounting hole 214, the socket portion 212 and the outer body structure are fixed to each other, thereby mounting the first mounting portion 21 of the quick release assembly 20 on the outer body structure, and the quick release is also facilitated by such a connection manner. The assembly 20 is detached from the outer body structure. Of course, the first mounting portion 21 of the quick-release assembly 20 can also be connected to the external main structure by other connecting means (which may be a fixed connection or a detachable connection), which is not limited in the embodiment of the present invention.

In an optional embodiment, the second mounting portion 22 of the quick release assembly 20 includes two limiting portions 25 and a connecting portion 26 between the two limiting portions 25 . The limiting portion 25 is provided with the fixing member 24 , and the connecting portion 26 defines the slot 23 . In this embodiment, the two limiting portions 25 are spaced apart from the connecting portion 26, and when the slot 23 is processed, a rounded corner is formed at the bottom of the slot 23, which may hinder the plugging portion 11 from being inserted into the slot. In the slot 23, the rounding may be milled through the interval between the two limiting portions 25 and the connecting portion 26, so that the plug portion 11 is inserted into the slot 23 and closely matched with the slot 23. At the same time, it is convenient to observe the position of the insertion portion 11 from the gap between the limiting portion 25 and the connecting portion 26 so as to insert the insertion portion 11 into the slot 23. Moreover, the distance between the two limiting portions 25 is equal to the width of the insertion portion 11, and the insertion portion 11 can be guided to facilitate the insertion of the insertion portion 11 into the slot 23. Of course, in other examples, the two limiting portions 25 and the connecting portion 26 may also be integrally formed. In addition, the width of the portion of the main body portion 14 of the landing gear 10 adjacent to the insertion portion 11 is larger than the width of the insertion portion 11, and when the insertion portion 11 is inserted into the slot 23 of the connection portion 26, the main body portion is inserted into the position. 14 can abut against the limiting portion 25 to make the landing gear 10 more securely mounted.

In an optional embodiment, the sidewalls of the two limiting portions 25 are respectively provided with a connecting hole 251, and the connecting holes 251 of the two limiting portions 25 are coaxially disposed, and the two The fixing member 24 is bored in the connecting hole 251. In the present embodiment, the fixing member 24 is a ball plunger, and the insertion portion 11 is symmetrically disposed with the fixing member 24 of the ball plunger adjacent to both end portions of the two limiting portions 25 . The arcuate recess 12 is fitted. Further, in order to enhance the structural strength of the second mounting portion 22, the side portion of the connecting portion 26 is provided with a reinforcing flap 27 connected to the first mounting portion 21.

Normally, the ball head of the ball plunger is partially protruded from the side wall of the limiting portion 25, and when the insertion portion 11 of the landing gear 10 is inserted into the slot 23 of the connecting portion 26, the plug is inserted. The portion 11 first presses the ball head of the ball plunger to press the ball head into the connecting hole 251 of the side wall of the limiting portion 25, and when the arcuate recess portion 12 of the plug portion 11 moves to the connecting hole 251 In the corresponding position, the ball head of the ball plunger gradually pops out the connecting hole 251 until it completely engages with the arcuate recess 12, so that both sides of the plug portion 11 are engaged with the corresponding fixing members 24, thereby realizing The landing gear 10 and the second mounting portion 22 of the quick release assembly 20 are fixed to each other. When the landing gear 10 needs to be removed, the insertion portion 11 can be pulled out of the slot 23 of the connecting portion 26, thereby achieving quick disassembly and assembly of the landing gear 10 and the quick release assembly 20.

In an alternative embodiment, in order to simultaneously ensure the structural strength and weight reduction requirements of the landing gear 10, the landing gear 10 employs a 4 mm thick carbon fiber material to ensure the structural strength of the landing gear 10. The landing gear 10 is generally swept-shaped, dynamic and has good aerodynamic performance. The main body portion 14 of the landing gear 10 is provided with a plurality of hollow portions 13 along its longitudinal direction, so that the requirement for weight reduction can be ensured. The components of the quick release assembly 20 can be made of an aluminum alloy material, which also ensures the structural strength and weight reduction requirements.

Referring to FIG. 4 and FIG. 5, an embodiment of the present invention further provides a drone 200, which may be a fixed-wing UAV, a multi-rotor UAV, a vertical take-off and landing fixed-wing UAV, and a hybrid wing UAV. And other aircraft model equipment. In the example shown in the figure, the drone 200 is a vertical take-off and landing fixed-wing drone, and the drone 200 includes a fuselage 91, an arm 92 disposed on the fuselage 91, a fixed wing 93, and an installation. The landing gear structure 100 of the arm 92. Optionally, the tail portion of the fuselage 91 is further provided with a propeller 94 as a power unit of the fixed wing 93, and the fixed wing 93 is detachably mounted on the body 91. It should be noted that the descriptions of the landing gear structure 100 in the above embodiments and embodiments are also applicable to the drone 200 of the embodiment of the present invention. The first mounting portion 21 of the quick release assembly 20 of the landing gear structure 100 is coupled to the arm 92.

In the UAV 200 of the embodiment of the present invention, the landing gear 10 of the landing gear structure 100 is inserted into the slot 23 of the second mounting portion 22 of the quick release assembly 20 through the plug portion 11, and then passed through the fixing member 24 and the second The mounting portion 22 is fixedly coupled to the quick release assembly 20, and then coupled to the arm 92 of the drone 200 through the first mounting portion 21 of the quick release assembly 20, thereby mounting the landing gear 10 to the arm 92. When the landing gear 10 needs to be disassembled, the insertion portion 11 of the landing gear 10 is pulled out from the slot 23 of the second mounting portion 22 of the quick release unit 20, and the disengagement of the landing gear 10 and the arm 92 is completed. The structure is simple, reliable, and easy to disassemble.

As shown in FIG. 4 to FIG. 6 , in an optional embodiment, the number of the arms 92 is two, symmetrically disposed on two sides of the body 91 , and each arm 92 is provided with two The landing gear structure 100, the two landing gear structures 100 are disposed one after the other on the corresponding arm 92, and the landing gear structures 100 disposed on the two arms 92 are inclined outwardly with respect to the axial direction of the fuselage 91. The arrangement is arranged in an outer "eight" shape, which can greatly increase the stability of the whole machine when the drone 200 is placed on the ground.

Referring to FIG. 7 , in an optional embodiment, the top of the fuselage 91 is provided with a receiving cavity for accommodating electronic components, and the opening of the receiving cavity is detachably covered with a hatch cover 95 and a hatch cover. The inner wall of the 95 is provided with a lining 96, and the lining 96 is partially protruded from the hatch 95. The hatch cover 95 is attached to the body 91 to cover the receiving cavity, and the electronic component can be enclosed inside the body 91. The electronic components may include components such as a battery, a GPS module, a 4G module, a satellite module, a main control module, and the like. Alternatively, the hatch cover 95 and the body 91 may be detachably connected by a snap structure such as a snap fastener.

By providing a portion of the inner wall of the hatch 95 that protrudes from the lining 96 of the hatch 95, the connection area between the hatch 95 and the body 91 can be increased. When the hatch 95 is coupled to the fuselage 91, the portion of the lining 96 that protrudes from the hatch 95 can be filled to form a stop at the gap between the hatch 95 and the fuselage 91, thereby ensuring the hatch 95 and the fuselage 91. There is no break between installations to avoid the hatch cover 95 being detached from the fuselage 91 during flight of the drone 200.

The above is only a preferred embodiment of the present invention, and is not intended to limit the embodiments of the present invention. The embodiments of the present invention have been disclosed in the preferred embodiments, but are not intended to limit the implementation of the present invention. For example, those skilled in the art can make some modifications or modifications to the equivalent embodiments by using the above-disclosed technical contents without departing from the technical scope of the embodiments of the present invention. Any simple modifications, equivalent changes and modifications to the above embodiments in accordance with the technical solutions of the embodiments of the present invention are still within the scope of the technical solutions of the embodiments of the present invention.

The disclosure of this patent document contains material that is subject to copyright protection. This copyright is the property of the copyright holder. The copyright owner has no objection to the reproduction of the patent document or the patent disclosure in the official records and files of the Patent and Trademark Office.

Claims

A landing gear structure, comprising: a landing gear and a quick release assembly;

The landing gear includes a main body portion and a plug portion provided at the main body portion, the quick release assembly including a first mounting portion for connecting with the outer main body structure and a second mounting connected to the first mounting portion The second mounting portion is provided with a slot and a fixing member that cooperate with the plug portion;

The insertion portion is inserted into the slot and fixed to the second mounting portion by the fixing member.
The landing gear structure according to claim 1, wherein the first mounting portion includes a socket portion that is sleeved on the outer body structure, and the outer side wall of the socket portion is connected to the second mounting portion. unit.
The landing gear structure according to claim 1, wherein the second mounting portion comprises two limiting portions and a connecting portion between the two limiting portions; In the fixing member, the connecting portion opens the slot.
The landing gear structure according to claim 3, wherein the two limiting portions are spaced apart from the connecting portion.
The landing gear structure according to claim 3, wherein a spacing distance between the two limiting portions is equal to a width of the insertion portion.
The landing gear structure according to claim 3, wherein the side walls of the two limiting portions are respectively provided with connecting holes, and the connecting holes of the two limiting portions are coaxially disposed, and two The fixing member is worn in each of the connecting holes.
The landing gear structure according to claim 3, wherein the fixing member is a ball plunger.
The landing gear structure according to claim 7, wherein the insertion portion is symmetrically disposed with arcuate recesses adjacent to both end portions of the two limiting portions to cooperate with the fixing member.
The landing gear structure according to claim 3, wherein the side portion of the connecting portion is provided with a reinforcing flap connected to the first mounting portion.
The landing gear structure of claim 1 wherein said landing gear is a swept-back landing gear.
The landing gear structure according to claim 1, wherein the main body portion is provided with a plurality of hollow portions along a length direction thereof.
An unmanned aerial vehicle, comprising: a fuselage, an arm disposed on the fuselage, and a landing gear structure, comprising: a landing gear and a quick release assembly;

The landing gear includes a main body portion and a plug portion provided at the main body portion, the quick release assembly including a first mounting portion for connecting with the outer main body structure and a second mounting connected to the first mounting portion The second mounting portion is provided with a slot and a fixing member that cooperate with the plug portion;

The insertion portion is inserted into the slot and fixed to the second mounting portion by the fixing member, and the first mounting portion of the quick release assembly of the landing gear structure is connected to the arm.
The drone according to claim 12, wherein the first mounting portion includes a socket portion that is sleeved on the outer body structure, and the outer side wall of the socket portion is connected to the second mounting portion. unit.
The drone according to claim 12, wherein the second mounting portion includes two limiting portions and a connecting portion between the two limiting portions; the limiting portion is mounted In the fixing member, the connecting portion opens the slot.
The drone according to claim 14, wherein the two limiting portions are spaced apart from the connecting portion.
The drone according to claim 14, wherein a distance between said two limiting portions is equal to a width of said insertion portion.
The UAV according to claim 14, wherein the side walls of the two limiting portions are respectively provided with connecting holes, and the connecting holes of the two limiting portions are coaxially disposed, and two The fixing member is worn in each of the connecting holes.
The drone according to claim 14, wherein the fixing member is a ball plunger.
The unmanned aerial vehicle according to claim 18, wherein the insertion portion is symmetrically disposed with arcuate recesses adjacent to both end portions of the two limiting portions to engage with the fixing member.
The drone according to claim 14, wherein the side portion of the connecting portion is provided with a reinforcing flap connected to the first mounting portion.
The drone according to claim 12, wherein said landing gear is a swept-back landing gear.
The drone according to claim 12, wherein the main body portion is provided with a plurality of hollow portions along its longitudinal direction.