CN211196598U

CN211196598U - A collapsible undercarriage for unmanned aerial vehicle

Info

Publication number: CN211196598U
Application number: CN201922165413.6U
Authority: CN
Inventors: 曹庆旭; 庞振岳; 赵学松; 孔令超; 李楠; 佟亮; 裴允嘉
Original assignee: Shenyang Xuanfei Aviation Technology Co ltd
Current assignee: Shenyang Xuanfei Aviation Technology Co ltd
Priority date: 2019-12-06
Filing date: 2019-12-06
Publication date: 2020-08-07
Anticipated expiration: 2029-12-06

Abstract

The application provides a foldable undercarriage for an unmanned aerial vehicle, which comprises a first folding support and a second folding support, wherein the first folding support is positioned on one side of a body of the unmanned aerial vehicle, the second folding support corresponds to the first folding support and is positioned on the other side of the body of the unmanned aerial vehicle, and two pull rods are connected between the first folding support and the second folding support; the first folding bracket can be folded towards the second folding bracket by the first folding mechanism to be in a state parallel to the pull rod; the second folding bracket can be folded towards the first folding bracket by the second folding mechanism to be in a state parallel to the pull rod. This application is through setting up beta structure on the first folding support of the both sides of the fuselage of unmanned aerial vehicle and the second folding support for first folding support and second folding support can be folding each other relatively. This application owing to need not to dismantle from unmanned aerial vehicle, can directly fold and reduce the volume, also very conveniently resumes into the user state from fold condition moreover, has improved unmanned aerial vehicle's warehousing and transportation efficiency greatly.

Description

A collapsible undercarriage for unmanned aerial vehicle

Technical Field

The application relates to the technical field of unmanned aerial vehicles, especially relates to an unmanned aerial vehicle undercarriage, in particular to a collapsible undercarriage for unmanned aerial vehicle.

Background

CN 206278267U discloses a multi-rotor unmanned aerial vehicle, the unmanned aerial vehicle of this prior art sets up to make adjacent paddle not be in same horizontal plane for thereby reduce the wheel base of many rotor aircrafts and alleviate complete machine weight, improve duration. However, the upper part of the undercarriage in the prior art is too close to the middle part of the fuselage, so that the included angle area of the undercarriage is too narrow, and the load with larger volume cannot be carried.

For solving above-mentioned prior art's defect, CN 107600391A discloses an electronic unmanned aerial vehicle undercarriage, and this prior art adopts adapter sleeve's form to be convenient for connect through the screw, and simple structure and easily make and equipment have reduced the cost and have improved unmanned aerial vehicle's production efficiency.

Further, CN 209258386U has proposed an improved unmanned aerial vehicle undercarriage on this basis again, and it has adopted the quick detach structure of the dismouting of being convenient for, and simple structure is reliable, and it is convenient to dismantle, save time when being favorable to the dismouting operation, reduces intensity of labour.

This prior art effectively overcomes the deficiencies of the prior art, but there is still room for improvement. Especially when needing to reduce the unmanned aerial vehicle volume and carry out the rapid transit, still need further improvement with the efficiency of all undercarriage dismantlements examining and repairing, change, transportation, dismantle into independent part after all with the undercarriage, also very time consuming when the equipment.

Disclosure of Invention

The technical problem that this application will be solved is to provide a collapsible undercarriage for unmanned aerial vehicles to reduce or avoid the aforementioned problems.

In order to solve the technical problem, the application provides a foldable undercarriage for an unmanned aerial vehicle, which is used for being installed on two sides below a fuselage of the unmanned aerial vehicle and comprises a first folding support located on one side of the fuselage of the unmanned aerial vehicle and a second folding support corresponding to the first folding support and located on the other side of the fuselage of the unmanned aerial vehicle, wherein two pull rods are connected between the first folding support and the second folding support; a first folding mechanism is arranged below the position, connected with the pull rod, of the first folding support, and the first folding support can be folded towards the second folding support through the first folding mechanism to be in a state parallel to the pull rod; and a second folding mechanism is arranged below the position, connected with the pull rod, of the second folding support, and the second folding support can be folded towards the first folding support to be parallel to the pull rod through the second folding mechanism.

Preferably, the vertical distance between the first folding mechanism and the pull rod is smaller than the vertical distance between the second folding mechanism and the pull rod.

Preferably, the first folding bracket is adjacent to the pull rod after being folded; after the second folding support is folded, the second folding support is close to the first folding support, and the first folding support is clamped between the second folding support and the pull rod.

Preferably, the first folding bracket comprises two vertical rods connected with the machine body and a cross rod arranged at the tail ends of the vertical rods; the two vertical rods are respectively connected with one pull rod; and the two vertical rods of the first folding support are respectively provided with one first folding mechanism below the position connected with the pull rod.

Preferably, the first folding mechanisms on the two vertical bars of the first folding bracket and the corresponding pull rods are in the same horizontal plane.

Preferably, the second folding support comprises two vertical rods connected with the machine body and a cross rod arranged at the tail ends of the vertical rods; the two vertical rods are respectively connected with one pull rod; and the two vertical rods of the second folding support are respectively provided with one second folding mechanism below the position connected with the pull rod.

Preferably, the second folding mechanisms on the two vertical bars of the second folding support and the corresponding pull rods are in the same horizontal plane.

This application is through setting up beta structure on the first folding support of the both sides of unmanned aerial vehicle's fuselage and the second folding support for first folding support and second folding support can be folding each other relatively, and the pull rod between the two is generally parallel relatively to first folding support and the second folding support after folding, has reduced the volume of undercarriage greatly. The utility model provides a collapsible undercarriage owing to need not to dismantle from unmanned aerial vehicle, can directly fold and reduce the volume, also very conveniently resumes into the user state from fold condition moreover, has improved unmanned aerial vehicle's warehousing and transportation efficiency greatly.

Drawings

The drawings are only for purposes of illustrating and explaining the present application and are not to be construed as limiting the scope of the present application. Wherein the content of the first and second substances,

FIG. 1 shows a schematic view of a collapsible landing gear according to a specific embodiment of the present application;

figures 2 and 3 show schematic views of the collapsible landing gear of figure 1 in a collapsed state from different perspectives.

Detailed Description

In order to more clearly understand the technical features, objects, and effects of the present application, embodiments of the present application will now be described with reference to the accompanying drawings. Wherein like parts are given like reference numerals.

As described in the background art, the undercarriage in the prior art has a quick-dismounting function, and the whole undercarriage can be dismounted for maintenance, replacement and transportation when needed. However, the prior art unmanned aerial vehicle landing gear needs to be disassembled into independent parts for transportation, and the subsequent assembly is troublesome. Therefore, this application provides a collapsible undercarriage for unmanned aerial vehicle, it need not to dismantle from unmanned aerial vehicle, can directly fold and reduce the volume, also is convenient for resume into the user state from fold condition, has improved unmanned aerial vehicle's warehousing and transportation efficiency.

As shown in fig. 1, the foldable landing gear of the present application is also used for being installed at two sides below a fuselage (not shown in the figure) of the unmanned aerial vehicle, that is, two sides of the fuselage are respectively and symmetrically provided with one landing gear, and a pull rod 27 for reinforcing the structure is additionally arranged between the two landing gears compared with the prior art. In which figure 1 shows a schematic view of a foldable landing gear according to a particular embodiment of the present application. It will be appreciated by those skilled in the art that the improved landing gear of the present application may be provided on the same drone as disclosed in CN 209258386U, or on any of the drones.

For convenience of explanation of the structure and folding principle of the foldable landing gear of the present application, in the following description, a landing gear on one side of the body of the drone is defined as a first folding bracket 20, a landing gear on the other side of the body of the drone corresponding to the first folding bracket 20 is defined as a second folding bracket 30, and the structures of the first folding bracket 20 and the second folding bracket 30 are substantially the same, and two pull rods 27 are connected therebetween. That is, by definition, the foldable undercarriage of the present application comprises a first folding support 20 located on one side of the fuselage of the drone, and a second folding support 30 located on the other side of the fuselage of the drone, corresponding to the first folding support 20, between which two tie rods 27 are connected between the first folding support 20 and the second folding support 30. The above structure is in fact substantially the same as the unmanned aircraft landing gear mentioned in the background, with the difference that the first folding leg 20 and the second folding leg 30 of the collapsible landing gear of the present application both have a collapsible structure, and that the first folding leg 20 and the second folding leg 30 can be collapsed in a specific manner, which can significantly reduce the bulk of the landing gear.

The collapsible structure of the present application as an improvement over the prior art is described in further detail below with reference to fig. 1-3, and as to structures not described in the present application, those skilled in the art can understand with reference to the drawings and the prior art. In which figures 2 and 3 show, in different views, a schematic view of the collapsible landing gear of figure 1 in a collapsed state.

As shown in the drawings, in one embodiment of the present application, the first folding bracket 20 is provided with a first folding mechanism 212 below the position where it is connected to the draw bar 27, and the first folding bracket 20 can be folded toward the second folding bracket 30 by the first folding mechanism 212 to a state substantially parallel to the draw bar 27; the second folding bracket 30 is provided with a second folding mechanism 213 below the position where it is connected to the draw bar 27, and the second folding bracket 30 can be folded toward the first folding bracket 20 by the second folding mechanism 213 to a state substantially parallel to the draw bar 27. The state after the first folding brackets 20 and the second folding brackets 30 are folded is shown in fig. 2 and 3. The first folding mechanism 212 and the second folding mechanism 213 may be any folding mechanism suitable for connecting and folding the rods, such as a folder of a foldable bicycle, etc., which can be used in the concept of the present application.

In the particular embodiment shown in fig. 2 and 3, the first folding bracket 20 is folded next to the tie rod 27; the second folding bracket 30 is folded next to the first folding bracket 20 and the first folding bracket 20 is sandwiched between the second folding bracket 30 and the draw bar 27. That is, in the illustrated embodiment, the first folding leg 20 is folded first, and then the second folding leg 30 is folded. To ensure that the folding does not interfere, the vertical distance between the first folding mechanism 212 and the pull rod 27 is preferably smaller than the vertical distance between the second folding mechanism 213 and the pull rod 27.

Further, as shown in the drawings, the first folding bracket 20 and the second folding bracket 30 of the present application each include two vertical bars 21 connected to the body and a cross bar 22 disposed at the end of the vertical bar 21, and the upper ends of the two vertical bars 21 are fixedly connected to the body. Specifically, the first folding bracket 20 includes two vertical bars 21 connected to the body and a cross bar 22 disposed at the end of the vertical bars 21; the two vertical rods 21 are respectively connected with a pull rod 27; the two vertical rods 21 of the first folding bracket 20 are each provided with a first folding mechanism 212 below the position of connection with the pull rod 27. The second folding bracket 30 also comprises two vertical rods 21 connected with the machine body and a cross rod 22 arranged at the tail ends of the vertical rods 21; the two vertical rods 21 are respectively connected with a pull rod 27; the two vertical rods 21 of the second folding bracket 30 are each provided with a second folding mechanism 213 below the position of connection with the tie rod 27.

Also to avoid folding interference, it is preferable for the first folding means 212 on the two vertical bars 21 of the first folding bracket 20 to be in the same horizontal plane as the corresponding tie bar 27. The second folding mechanisms 213 on the two vertical bars 21 of the second folding support 30 are in the same horizontal plane as the corresponding tie rods 27.

To sum up, this application is through setting up beta structure on first folding support and the second folding support in the both sides of unmanned aerial vehicle's fuselage for first folding support and second folding support can be folded each other relatively, and the first folding support after folding and the second folding support can be generally parallel relatively the pull rod between the two, have reduced the volume of undercarriage greatly. The utility model provides a collapsible undercarriage owing to need not to dismantle from unmanned aerial vehicle, can directly fold and reduce the volume, also very conveniently resumes into the user state from fold condition moreover, has improved unmanned aerial vehicle's warehousing and transportation efficiency greatly.

It should be appreciated by those skilled in the art that while the present application is described in terms of several embodiments, not every embodiment includes only a single embodiment. The description is thus given for clearness of understanding only, and it is to be understood that all matters in the embodiments are to be interpreted as including all technical equivalents which are encompassed by the claims and are to be interpreted as combined with each other in a different embodiment so as to cover the scope of the present application.

The above description is only illustrative of the present invention and is not intended to limit the scope of the present invention. Any equivalent alterations, modifications and combinations that may be made by those skilled in the art without departing from the spirit and principles of this application shall fall within the scope of this application.

Claims

1. A foldable undercarriage for an unmanned aerial vehicle, which is used for being installed on two sides below a fuselage of the unmanned aerial vehicle, comprises a first folding bracket (20) positioned on one side of the fuselage of the unmanned aerial vehicle, and a second folding bracket (30) corresponding to the first folding bracket (20) and positioned on the other side of the fuselage of the unmanned aerial vehicle, wherein two pull rods (27) are connected between the first folding bracket (20) and the second folding bracket (30); the method is characterized in that: a first folding mechanism (212) is arranged below the position where the first folding bracket (20) is connected with the pull rod (27), and the first folding bracket (20) can be folded towards the second folding bracket (30) through the first folding mechanism (212) to be in a state parallel to the pull rod (27); the second folding support (30) is provided with a second folding mechanism (213) below a position connected with the pull rod (27), and the second folding support (30) can be folded towards the first folding support (20) through the second folding mechanism (213) to be parallel to the pull rod (27).

2. The foldable landing gear according to claim 1, wherein the first folding mechanism (212) is at a smaller vertical distance from the tie-rod (27) than the second folding mechanism (213).

3. Collapsible landing gear according to claim 2, wherein the first folding bracket (20) is folded next to the pull rod (27); the second folding support (30) is adjacent to the first folding support (20) after being folded, and the first folding support (20) is clamped between the second folding support (30) and the pull rod (27).

4. A foldable landing gear according to claim 3, wherein the first folding leg (20) comprises two vertical rods (21) connected to the fuselage and a cross-bar (22) arranged at the ends of the vertical rods (21); the two vertical rods (21) are respectively connected with one pull rod (27); the two vertical rods (21) of the first folding support (20) are respectively provided with one first folding mechanism (212) below the position connected with the pull rod (27).

5. A foldable landing gear according to claim 4, wherein the first folding mechanism (212) on the two vertical rods (21) of the first folding bracket (20) is in the same horizontal plane as the corresponding tie-rod (27).

6. A foldable landing gear according to claim 5, wherein the second folding leg (30) comprises two vertical rods (21) connected to the fuselage and a cross-bar (22) arranged at the ends of the vertical rods (21); the two vertical rods (21) are respectively connected with one pull rod (27); the two vertical bars (21) of the second folding bracket (30) are respectively provided with one second folding mechanism (213) below the position connected with the pull rod (27).

7. A foldable landing gear according to claim 6, wherein the second folding mechanism (213) on the two vertical bars (21) of the second folding bracket (30) is in the same horizontal plane as the corresponding tie-rods (27).