CN111619784A

CN111619784A - Unmanned aerial vehicle with folding wings

Info

Publication number: CN111619784A
Application number: CN202010601872.9A
Authority: CN
Inventors: 曹雷
Original assignee: Zhuhai Sv Tech Co ltd
Current assignee: Zhuhai Sv Tech Co ltd
Priority date: 2020-06-28
Filing date: 2020-06-28
Publication date: 2020-09-04

Abstract

An unmanned aerial vehicle with folding wings comprises an unmanned aerial vehicle body, a wing fixing base and a first wing connecting rod; the unmanned aerial vehicle body is provided with an accommodating groove with an opening at the top, the unmanned aerial vehicle body is also provided with a first fixing part, a wing fixing base is installed in the accommodating groove, the wing fixing base is also provided with a vertically arranged lifting slide rod, a first end of a first wing connecting rod is sleeved on the lifting slide rod, and a second end of the first wing connecting rod is provided with a rotor wing; the first wing connecting rod can lift along the lifting slide rod or rotate by taking the lifting slide rod as an axis, and has a first state of being matched and connected with the first fixing part and a second state of being separated from the first fixing part and moving to the accommodating groove for accommodating. This folding wing unmanned aerial vehicle's wing part can fold when need not the use and deposit, effectively reduces its occupation space, is convenient for transport and deposits.

Description

Unmanned aerial vehicle with folding wings

Technical Field

The invention relates to the field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle with folding wings.

Background

With the continuous progress of the science and technology society, the unmanned aerial vehicle trade is gradually becoming bigger and bigger, and many rotor crafts are fast owing to advantages such as mechanical structure is simple, and driving system is simple, can rise perpendicularly and descend, and the very young of researcher becomes radiant in time, and the many rotor crafts begin to be studied in dispute, all have the heat tide of commercialization of many rotors in the global scope.

The large-scale many rotor unmanned aerial vehicle that has now is when idle, and the extension radius of its wing frame is big, very occupation space to it is impaired because of the collision easily in the transportation, makes unmanned aerial vehicle's transportation inconvenient.

Disclosure of Invention

Technical problem to be solved

In order to solve the problems, the folding wing unmanned aerial vehicle provided by the invention can be folded and stored, so that the occupied space is effectively reduced.

(II) technical scheme

In order to achieve the purpose, the invention provides the following technical scheme: an unmanned aerial vehicle with folding wings comprises an unmanned aerial vehicle body, a wing fixing base and a first wing connecting rod; the unmanned aerial vehicle body is provided with an accommodating groove with an opening at the top, the unmanned aerial vehicle body is also provided with a first fixing part, a wing fixing base is installed in the accommodating groove, the wing fixing base is also provided with a vertically arranged lifting slide rod, a first end of a first wing connecting rod is sleeved on the lifting slide rod, and a second end of the first wing connecting rod is provided with a rotor wing; the first wing connecting rod can lift along the lifting slide rod or rotate by taking the lifting slide rod as an axis, and has a first state of being matched and connected with the first fixing part and a second state of being separated from the first fixing part and moving to the accommodating groove for accommodating.

Preferably, the first fixing portion is provided with a fixing groove, and the first wing connecting rod can be fastened in the fixing groove.

Preferably, the folding wing unmanned aerial vehicle further comprises a second wing connecting rod, wherein the first end of the second wing connecting rod is hinged with the second end of the first wing connecting rod, and the rotor wing is installed at the second end of the second wing connecting rod; when the first wing connecting rod is in the second state, the second wing connecting rod can be accommodated in the accommodating groove.

Preferably, the second end of the first wing connecting rod is further provided with a second fixing part, and the first end of the second wing connecting rod is further provided with a third fixing part; when the first wing connecting rod is in the first state, the second fixing part can be matched and connected with the third fixing part, so that the first wing connecting rod and the second wing connecting rod are relatively fixed.

Preferably, this folding wing unmanned aerial vehicle still includes the retaining member, and the retaining member is installed on first fixed part, and when first wing connecting rod was in the first state, the setting of first fixed part and first wing connecting rod can be penetrated to the retaining member to make first wing connecting rod be fixed in on the first fixed part.

Preferably, the second fixing portion and the third fixing portion are both provided with threaded holes, and the second fixing portion can be fixedly connected with the third fixing portion through bolts.

Preferably, the unmanned aerial vehicle body is polygonal prism shape setting, and the fixed slot is the cylindricality setting, and two first fixed parts that set up on two arbitrary relative lateral wall surfaces of unmanned aerial vehicle body, the central line of the fixed slot that is equipped with on it are in same straight line.

Preferably, still be equipped with the notch that the groove was accomodate in the switch-on the unmanned aerial vehicle body, the groove is accomodate to the second end of first wing connecting rod can stretch out from the notch.

Preferably, the wing fixing base is arranged on one side, far away from the notch, in the accommodating groove, and the length of the first wing connecting rod is greater than or equal to that of the accommodating groove.

Advantageous effects

The invention has the beneficial effects that: an unmanned aerial vehicle with folding wings comprises an unmanned aerial vehicle body, a wing fixing base and a first wing connecting rod; the unmanned aerial vehicle body is provided with an accommodating groove with an opening at the top, the unmanned aerial vehicle body is also provided with a first fixing part, a wing fixing base is installed in the accommodating groove, the wing fixing base is also provided with a vertically arranged lifting slide rod, a first end of a first wing connecting rod is sleeved on the lifting slide rod, and a second end of the first wing connecting rod is provided with a rotor wing; the first wing connecting rod can lift along the lifting slide rod or rotate by taking the lifting slide rod as an axis, and has a first state of being matched and connected with the first fixing part and a second state of being separated from the first fixing part and moving to the accommodating groove for accommodating. This folding wing unmanned aerial vehicle's wing part can fold when need not the use and deposit, effectively reduces its occupation space, is convenient for transport and deposits.

Drawings

The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention without limiting the invention in which:

FIG. 1 is a schematic diagram of a first state according to an embodiment of the present invention;

FIG. 2 is a diagram illustrating a second state of the embodiment of the present invention;

FIG. 3 is a schematic diagram of a portion of an embodiment of the present invention;

FIG. 4 is another schematic diagram of a portion of an embodiment of the present invention;

FIG. 5 is an enlarged view taken at A in FIG. 4;

FIG. 6 is a schematic view of the connection structure of the first wing connecting rod and the second wing connecting rod;

FIG. 7 is a schematic view of a linear arrangement of airfoils;

fig. 8 is a schematic structural view of the body of the unmanned aerial vehicle;

in the figure, 1 an unmanned aerial vehicle body, 2 wing fixing bases, 3 first wing connecting rods, 4 second wing connecting rods, 5 locking pieces, 10 accommodating grooves, 11 first fixing parts, 12 notches, 110 fixing grooves, 20 lifting slide rods, 200 limiting bosses, 30 second fixing parts, 40 third fixing parts and a rotor wings are arranged.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

Referring to fig. 1 to 6, an unmanned aerial vehicle with folding wings comprises an unmanned aerial vehicle body 1, a wing fixing base 2 and a first wing connecting rod 3; the unmanned aerial vehicle comprises an unmanned aerial vehicle body 1, a containing groove 10, a first fixing part 11, a fixing groove 110, a wing fixing base 2, a lifting slide rod 20, a first wing connecting rod 3 and a rotor a, wherein the containing groove 10 is formed in the top opening of the unmanned aerial vehicle body 1, the first fixing part 11 is arranged on the first fixing part 11, the wing fixing base 2 is installed in the containing groove 10, the wing fixing base 2 is also provided with the lifting slide rod 20 which is vertically arranged, the first end of the first wing connecting rod 3 is sleeved on the lifting slide rod 20; the first wing connecting rod 3 can be lifted along the lifting slide bar 20 or rotate by taking the lifting slide bar 20 as an axis, and the first wing connecting rod 3 can be buckled in the fixed groove 110; the first wing link 3 has a first state of being engaged with the first fixing portion 11 and a second state of being separated from the first fixing portion 11 and moving into the receiving groove 10 for receiving.

In the present invention, the first wing connecting rod 3 and the first fixing portion 11 may be fixedly connected by a bolt. Specifically, in the embodiment of the present invention, the fixing groove 110 is opened at a side of the first fixing portion 11, so that the fixing groove 110 has a side-opened "U" shape. In a normal state, the first wing link 3 is fastened in the fixing groove 110, and at this time, the first fixing portion 11 also plays a role of supporting the first wing link 3. When need not to use this folding wing unmanned aerial vehicle, accessible external force makes first wing connecting rod 3 break away from fixed slot 110, later first wing connecting rod 3 uses lifting slide bar 20 to swing to the top of accomodating groove 10 as the axle center, again along lifting slide bar 20 gliding to accomodating in the groove 10 to folding and accomodating work are carried out first wing connecting rod 3, reduce the space occupancy of first wing connecting rod 3, effectively reduce this folding wing unmanned aerial vehicle's occupation space. Through the lift slide bar 20 of vertical setting, make first wing connecting rod 3 can descend and accomodate in the groove 10 or rise out and accomodate the groove 10 after use, cooperate side open-ended "U" shape fixed slot 110, can this folding wing unmanned aerial vehicle's of effectual improvement structural stability. It should be noted that, in the present invention, the top of the lifting slide rod 20 is further provided with a limit boss 200, and when the first wing connecting rod 3 is fastened to the fixing groove 110, the first wing connecting rod 3 is further abutted against the limit boss 200. And the size of the notch of the fixing groove 110 is slightly smaller than the size of the shaft of the first wing link 3, so that the first wing link 3 needs to enter the fixing groove 110 in a snap-fit manner, thereby further improving the connection stability of the first wing link 3 and the first fixing part 11.

Furthermore, in order to reduce the occupied space of the wing part of the folding wing unmanned aerial vehicle as much as possible, the folding wing unmanned aerial vehicle further comprises a second wing connecting rod 4, the first end of the second wing connecting rod 4 is hinged with the second end of the first wing connecting rod 3, a rotor a is installed at the second end of the second wing connecting rod 4, and the first wing connecting rod 3, the second wing connecting rod 4 and the rotor a form the wing part of the folding wing unmanned aerial vehicle; when the first wing connecting rod 3 is in the second state, the second wing connecting rod 4 can be stored in the storage groove 10, so that the wing part of the folding wing unmanned aerial vehicle can be folded for the second time and stored in the storage groove 10. It should be noted that, in the present invention, the rotor a can also be folded and overlapped, and even can be folded and stored in the storage slot 10, so as to further reduce the occupied space of the wing part.

Further, a second fixing portion 30 is further disposed at the second end of the first wing connecting rod 3, and a third fixing portion 40 is further disposed at the first end of the second wing connecting rod 4; when the first wing connecting rod 3 is in the first state, the second fixing portion 30 can be connected with the third fixing portion 40 in a matching manner, so that the first wing connecting rod 3 and the second wing connecting rod 4 are relatively fixed. The second fixing portion 30 and the third fixing portion 40 are each provided with a screw hole, and the second fixing portion 30 may be fixedly connected with the third fixing portion 40 by a bolt. The bolt is matched with the hinged shaft of the first wing connecting rod 3 and the hinged shaft of the second wing connecting rod 4 to be fixed in two points, the structural stability of the wing part of the folding wing unmanned aerial vehicle is improved, and the wings are prevented from loosening or shaking during operation to cause flight accidents.

Further, this folding wing unmanned aerial vehicle still includes retaining member 5, and retaining member 5 installs on first fixed part 11, and when first wing connecting rod 3 was in the first state, retaining member 5 can pierce through first fixed part 11 and the setting of first wing connecting rod 3 to make first wing connecting rod 3 be fixed in on the first fixed part 11. In the embodiment of the present invention, the locking member 5 is provided with a thread, and the locking member 5 sequentially penetrates through and is in threaded connection with the first fixing portion 11 and the first wing link 3, so that the connection stability of the first wing link 3 and the first fixing portion 11 can be further increased. However, in the present invention, the locking member 5 may be provided in plurality.

Further, as shown in fig. 7 and 8, in order to ensure the balance of the folding wing unmanned aerial vehicle, two wings which are opposite to each other at will need to be on the same straight line, in an embodiment of the present invention, the unmanned aerial vehicle body 1 is disposed in a polygonal prism shape, the fixing grooves 110 are disposed in a cylindrical shape, two first fixing portions 11 are disposed on two side wall surfaces which are opposite to each other at will of the unmanned aerial vehicle body 1, and center lines of the fixing grooves 110 disposed thereon are on the same straight line. Therefore, the fixing grooves 110 on the two first fixing portions 11 which are arranged oppositely are located on the same straight line, so that the two first wing connecting rods 3 to be installed on the two fixing grooves 110 are located on the same straight line, and therefore the flight balance of the folding wing unmanned aerial vehicle is guaranteed.

Further, since the length of the accommodating groove 10 is limited by the length of the sidewall of the fuselage of the unmanned aerial vehicle, and the fuselage of the unmanned aerial vehicle is generally smaller than the extension size of the wings thereof for reducing the weight, the length of the first wing connecting rod 3 may be greater than the length of the accommodating groove 10, so that the first wing connecting rod 3 cannot be accommodated into the accommodating groove 10 after being folded. In order to enable the length of the wings not to be limited by the length of the accommodating groove 10, in the embodiment of the invention, the unmanned aerial vehicle body 1 is further provided with a notch 12 communicated with the accommodating groove 10, and the second end of the first wing connecting rod 3 can extend out of the accommodating groove 10 from the notch 12, so that the accommodating work of the first wing connecting rod 3 with a longer size is facilitated.

It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.

The relative arrangement of the components and steps, the numerical expressions, and numerical values set forth in these embodiments do not limit the scope of the present application unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.

In the description of the present application, it is to be understood that the orientation or positional relationship indicated by the directional terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal" and "top, bottom", etc., are generally based on the orientation or positional relationship shown in the drawings, and are used for convenience of description and simplicity of description only, and in the case of not making a reverse description, these directional terms do not indicate and imply that the device or element being referred to must have a particular orientation or be constructed and operated in a particular orientation, and therefore, should not be considered as limiting the scope of the present application; the terms "inner and outer" refer to the inner and outer relative to the profile of the respective component itself.

Spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.

It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, the scope of protection of the present application is not to be construed as being limited.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. An unmanned aerial vehicle with folding wings is characterized by comprising an unmanned aerial vehicle body (1), a wing fixing base (2) and a first wing connecting rod (3);

the unmanned aerial vehicle comprises an unmanned aerial vehicle body (1), a containing groove (10) with an opening at the top is formed in the unmanned aerial vehicle body (1), a first fixing part (11) is further arranged on the unmanned aerial vehicle body (1), a wing fixing base (2) is installed in the containing groove (10), a lifting slide rod (20) is further vertically arranged on the wing fixing base (2), a first end of a first wing connecting rod (3) is sleeved on the lifting slide rod (20), and a rotor (a) is installed at a second end of the first wing connecting rod (3);

the first wing connecting rod (3) can ascend and descend along the ascending and descending slide rod (20) or rotate by taking the ascending and descending slide rod (20) as an axis, and the first wing connecting rod (3) has a first state of being connected with the first fixing part (11) in a matched mode and a second state of being separated from the first fixing part (11) and moving into the accommodating groove (10) to be accommodated.

2. A folding wing according to claim 1, characterized in that the first fastening part (11) is provided with a fastening groove (110), and the first wing connecting rod (3) can be fastened in the fastening groove (110).

3. A folding wing according to claim 1, further comprising a second wing connecting rod (4), wherein a first end of the second wing connecting rod (4) is hinged to a second end of the first wing connecting rod (3), and the rotor (a) is mounted to the second end of the second wing connecting rod (4); when the first wing connecting rod (3) is in the second state, the second wing connecting rod (4) can be accommodated in the accommodating groove (10).

4. A folding wing according to claim 3, characterized in that the second end of the first wing link (3) is further provided with a second fastening portion (30), and the first end of the second wing link (4) is further provided with a third fastening portion (40); when the first wing connecting rod (3) is in the first state, the second fixing part (30) can be matched and connected with the third fixing part (40) so as to relatively fix the first wing connecting rod (3) and the second wing connecting rod (4).

5. A folding wing according to claim 1, characterized in that it further comprises a locking element (5), the locking element (5) being mounted on the first fixing portion (11), the locking element (5) being arrangeable through the first fixing portion (11) and the first wing connecting rod (3) when the first wing connecting rod (3) is in the first state, so that the first wing connecting rod (3) is fixed to the first fixing portion (11).

6. A folding wing according to claim 4, characterized in that the second fastening part (30) and the third fastening part (40) are provided with threaded holes, and the second fastening part (30) can be fixedly connected to the third fastening part (40) by means of bolts.

7. The folding wing as claimed in claim 2, wherein the main body (1) of the unmanned aerial vehicle is in a polygonal prism shape, the fixing slots (110) are in a cylindrical shape, and the central lines of the fixing slots (110) on the two first fixing portions (11) arranged on any two opposite side wall surfaces of the main body (1) of the unmanned aerial vehicle are in the same straight line.

8. A folding wing according to claim 1, wherein the drone body (1) is further provided with a notch (12) communicating with the receiving slot (10), and the second end of the first connection rod (3) can extend out of the receiving slot (10) from the notch (12).

9. A folding wing according to claim 8, characterized in that the wing fastening base (2) is arranged in the receiving groove (10) on the side remote from the slot opening (12), and the length of the first wing connecting rod (3) is greater than or equal to the length of the receiving groove (10).