CN214216122U

CN214216122U - Folded form unmanned aerial vehicle

Info

Publication number: CN214216122U
Application number: CN202022790454.7U
Authority: CN
Inventors: 吴光润
Original assignee: Dongguan Sparkle Electronic Technology Co ltd
Current assignee: Dongguan Sparkle Electronic Technology Co ltd
Priority date: 2020-11-26
Filing date: 2020-11-26
Publication date: 2021-09-17
Anticipated expiration: 2030-11-26

Abstract

The utility model discloses a folding type unmanned aerial vehicle, including fuselage, first connecting plate, second connecting plate, the wing flight body, aircraft mount, flying motor. Has the advantages that: the utility model has the advantages that the first connecting plate is hinged with the second connecting plate, so that the folding state of the body and the wing flying body can be realized, and the size of the whole unmanned aerial vehicle is effectively reduced after the folding, thereby facilitating the daily transportation of a user; the utility model discloses a first connecting plate can be dismantled with the second connecting plate and be connected for the fuselage can accomplish the stationary state fast with the wing flight body, and fixed time spent is short, and fixed efficiency is high, and the stationary stability is good, simultaneously, need not with the help of the instrument among the fixed process, and the operation is comparatively convenient.

Description

Folded form unmanned aerial vehicle

Technical Field

The utility model relates to an unmanned air vehicle technique field, concretely relates to folded form unmanned aerial vehicle.

Background

The unmanned plane is called unmanned plane for short, and is an unmanned plane operated by radio remote control equipment and a self-contained program control device. The machine has no cockpit, but is provided with an automatic pilot, a program control device and other equipment. The personnel on the ground, the naval vessel or the mother aircraft remote control station can track, position, remotely control, telemeter and digitally transmit the personnel through equipment such as a radar. The aircraft can take off like a common airplane under the radio remote control or launch and lift off by a boosting rocket, and can also be thrown into the air by a mother aircraft for flying. During recovery, the aircraft can land automatically in the same way as the common aircraft landing process, and can also be recovered by a parachute or a barrier net for remote control. Can be repeatedly used for many times. The method is widely used for aerial reconnaissance, monitoring, communication, anti-submergence, electronic interference and the like.

However, the wings of the existing unmanned aerial vehicle are long, so that the unmanned aerial vehicle is large in size and inconvenient to transport by a user. When the wing of unmanned aerial vehicle is dismantled and transported, it is big to dismantle work load to still need carry assembly and disassembly tools at any time when using unmanned aerial vehicle, thereby make the reuse comparatively loaded down with trivial details after the unmanned aerial vehicle dismouting.

SUMMERY OF THE UTILITY MODEL

For solving above-mentioned problem comprehensively, especially to the not enough that prior art exists, the utility model provides a folded form unmanned aerial vehicle can solve above-mentioned problem comprehensively.

In order to achieve the above object, the utility model adopts the following technical means:

the utility model provides a folding type unmanned aerial vehicle, includes the fuselage, the bottom of fuselage is provided with the aircraft mount, the aircraft mount is provided with two sets ofly, two sets of aircraft mount central symmetry, the aircraft mount is connected with the fuselage, the both ends top of the long limit direction of aircraft mount is equipped with the flying motor of rigid coupling, the wing junction of fuselage is equipped with the first connecting plate of rigid coupling, the outside of first connecting plate is provided with the wing flight body, the wing junction of the wing flight body is equipped with the second connecting plate of rigid coupling, one side of first connecting plate is articulated with one side of second connecting plate, a side of first connecting plate still can dismantle with a side of second connecting plate and be connected.

Furthermore, the size of the wing connecting surface of the fuselage is the same as that of the wing connecting surface of the wing flight body.

The beneficial effects of the aircraft are that, the stability after fuselage and wing flight body connection can be effectively improved in this kind of setting, unmanned aerial vehicle stable flight can be convenient for.

Furthermore, the mode that one side of first connecting plate and one side of second connecting plate can dismantle the connection is at least one in grafting, bonding, absorption connection.

The beneficial effects of the above are that, the compactness after first connecting plate and second connecting plate are connected can effectively be improved in this kind of setting, can effectively prevent that the phenomenon of rupture from taking place.

Furthermore, the aircraft fixing frame is a fixing frame internally provided with a power supply.

The beneficial effects are that, the loading capacity of the fuselage can be effectively improved by the arrangement, and meanwhile, the flying motor is convenient to take electricity, so that the working efficiency of the flying motor is effectively improved.

The utility model has the advantages that: the utility model has the advantages that the first connecting plate is hinged with the second connecting plate, so that the folding state of the body and the wing flying body can be realized, and the size of the whole unmanned aerial vehicle is effectively reduced after the folding, thereby facilitating the daily transportation of a user; the utility model discloses a first connecting plate can be dismantled with the second connecting plate and be connected for the fuselage can accomplish the stationary state fast with the wing flight body, and fixed time spent is short, and fixed efficiency is high, and the stationary stability is good, simultaneously, need not with the help of the instrument among the fixed process, and the operation is comparatively convenient.

Drawings

Fig. 1 is a schematic structural diagram of the present invention;

fig. 2 is a usage state diagram of the present invention.

Detailed Description

The technical solution of the present invention will be described clearly and completely with reference to the accompanying drawings, and obviously, the described embodiments are some, but not all embodiments of the present invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.

As shown in fig. 1-2, the utility model provides a folding type unmanned aerial vehicle, including fuselage 1, the bottom of fuselage 1 is provided with aircraft mount 5, aircraft mount 5 is provided with two sets ofly, and is two sets of 5 centrosymmetric aircraft mounts, aircraft mount 5 is connected with fuselage 1, the flying motor 6 of rigid coupling is equipped with at the both ends top of 5 long edge directions of aircraft mount, the wing junction of fuselage 1 is equipped with first connecting plate 2 of rigid coupling, the outside of first connecting plate 2 is provided with wing flight body 4, the wing junction of wing flight body 4 is equipped with the second connecting plate 3 of rigid coupling, one side of first connecting plate 2 is articulated with one side of second connecting plate 3, a side of first connecting plate 2 still can be dismantled with a side of second connecting plate 3 and be connected.

The size of the wing connecting surface of the fuselage 1 is the same as that of the wing connecting surface of the wing flying body 4. The stability after fuselage 1 and wing flight body 4 are connected can effectively be improved in this kind of setting, the unmanned aerial vehicle stable flight of can being convenient for.

The mode that a side of first connecting plate 2 and a side of second connecting plate 3 can be dismantled and be connected is at least one in grafting, bonding, absorption connection. The arrangement can effectively improve the compactness of the first connecting plate 2 after being connected with the second connecting plate 3, and can effectively prevent the occurrence of the fracture phenomenon.

The aircraft fixing frame 5 is a fixing frame internally provided with a power supply. The arrangement can effectively improve the loading capacity of the airplane body 1, and meanwhile, the flying motor 6 is convenient to take electricity, so that the working efficiency of the flying motor 6 is effectively improved.

The utility model relates to a folding type unmanned aerial vehicle, the utility model discloses a first connecting plate 2 is articulated with second connecting plate 3 for fuselage 1 and wing flight body 4 can realize fold condition, and folding unmanned aerial vehicle has effectively reduced holistic size, thereby convenient to use person daily transportation; the utility model discloses a first connecting plate 2 can be dismantled with second connecting plate 3 and be connected for fuselage 1 can accomplish the stationary state fast with wing flight body 4, and fixed time spent is short, and fixed efficient, the stationary stability is good, simultaneously, need not with the help of the instrument among the fixed process, and the operation is comparatively convenient.

The present invention is illustrated by way of example and not by way of limitation. It will be apparent to those skilled in the art that other variations and modifications of the present invention can be made in light of the above teachings, and it is not necessary or necessary to exhaustively enumerate all embodiments herein, and it is intended that all such obvious variations and modifications are within the scope of the present invention.

Claims

1. A folding unmanned aerial vehicle comprises a body (1), wherein an aircraft fixing frame (5) is arranged at the bottom end of the body (1), the aircraft fixing frames (5) are arranged in two groups, the two groups of the aircraft fixing frames (5) are centrosymmetric, the aircraft fixing frame (5) is connected with the fuselage (1), the tops of two ends of the aircraft fixing frame (5) in the long edge direction are provided with fixedly connected flying motors (6), it is characterized in that a first connecting plate (2) fixedly connected is arranged at the wing joint of the fuselage (1), the outer side of the first connecting plate (2) is provided with a wing flying body (4), the wing joint of the wing flying body (4) is provided with a second connecting plate (3) which is fixedly connected, one side of the first connecting plate (2) is hinged with one side of the second connecting plate (3), one side surface of the first connecting plate (2) is also detachably connected with one side surface of the second connecting plate (3).

2. The folding unmanned aerial vehicle of claim 1, wherein the wing connection surface of the fuselage (1) is the same size as the wing connection surface of the wing flight body (4).

3. The folding unmanned aerial vehicle of claim 1, wherein the detachable connection between one side of the first connecting plate (2) and one side of the second connecting plate (3) is at least one of insertion, adhesion and adsorption.

4. A folding drone according to claim 1, characterised in that the aircraft mount (5) is a mount with built-in power supply.