CN211519828U

CN211519828U - Foldable unmanned aerial vehicle's quick wing structure that expandes

Info

Publication number: CN211519828U
Application number: CN202020065308.5U
Authority: CN
Inventors: 郝伟
Original assignee: Binzhou University
Current assignee: Binzhou University
Priority date: 2020-01-14
Filing date: 2020-01-14
Publication date: 2020-09-18
Anticipated expiration: 2030-01-14

Abstract

The utility model provides a fast unfolding wing structure of a folding unmanned aerial vehicle, relating to the technical field of wings of unmanned aerial vehicles, in order to solve the problems of long unfolding time, asynchronous unfolding and not-in-place unfolding of the wings of the unmanned aerial vehicle, the motion camera is arranged at the side surface of one narrow side of the unmanned aerial vehicle chassis, the wing unfolding mechanism is arranged in the extension column groove, and due to the arrangement of the lifting mechanism, the wings fixed in the wing balance weight can rotate at high speed through the rotating shaft to play a lifting role, because the wing switch is arranged, the circular button in the wing switch can carry out vertical linear motion on the fixed column fixedly connected with the lower end surface of the circular button through the return spring at the lower part, because the wing unfolding mechanism is arranged, wherein the wing that sets up extends the post, and the minor arc sliding block that the wing extended post both sides set up can slide around the circular fixed column periphery of scarce formula in the interior.

Description

Foldable unmanned aerial vehicle's quick wing structure that expandes

Technical Field

The utility model belongs to the technical field of the unmanned aerial vehicle wing, more specifically say, in particular to foldable unmanned aerial vehicle's quick wing structure that expandes.

Background

Drones are unmanned aircraft that are operated by radio remote control devices and self-contained program control devices, or are operated autonomously, either completely or intermittently, by an on-board computer.

Drones tend to be more suitable for tasks that are too "fool, dirty, or dangerous" than are manned aircraft. Unmanned aerial vehicles can be classified into military and civil applications according to the application field. For military use, unmanned aerial vehicles divide into reconnaissance aircraft and target drone. In the civil aspect, the unmanned aerial vehicle + the industry application is really just needed by the unmanned aerial vehicle; at present, the unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, romantic manufacturing and the like, the application of the unmanned aerial vehicle is greatly expanded, and developed countries actively expand industrial application and develop unmanned aerial vehicle technology.

In the prior art, a folding wing unfolding mechanism is mostly driven by a spring, a motor, a steering engine and the like to unfold and is synchronous by means of gears and the like. The defects of long unfolding time, asynchronous unfolding process, incomplete unfolding, unreliable locking after unfolding, easy failure in long-term storage, complex structure and the like are not widely applied in practical application.

SUMMERY OF THE UTILITY MODEL

In order to solve the technical problem, the utility model provides a foldable unmanned aerial vehicle's quick wing structure that expandes to solve among the prior art folding wing expansion mechanism and use the drive such as spring, motor, steering wheel to expand mostly, and rely on gears etc. to guarantee in step. The problems that the unfolding time is long, the unfolding process is asynchronous, the unfolding is not in place, the locking after the unfolding is not reliable, the long-term storage is easy to lose efficacy, the structure is complex and the like are not widely applied in practical application.

The utility model discloses foldable unmanned aerial vehicle's the purpose and the efficiency of unfolding the wing structure fast, by following concrete technical means reach:

the utility model provides a foldable unmanned aerial vehicle's quick wing structure that expandes, includes unmanned aerial vehicle machine case, motion camera, wing expanding mechanism, unmanned aerial vehicle landing leg, the unmanned aerial vehicle landing leg is equipped with everywhere altogether, and terminal surface position under fixed connection is everywhere lifting mechanism respectively, unmanned aerial vehicle machine case upper end surface central point puts elastic connection has the wing switch, the motion camera sets up in unmanned aerial vehicle machine case narrow side position, wing expanding mechanism installs and extends the post inslot portion.

Furthermore, the lifting mechanism comprises wings, wing balance blocks and a rotating shaft, wherein the wing balance blocks are designed to be square blocks, the wings penetrate through the wing balance blocks, and the wing balance blocks are connected to the upper end face of the rotating shaft in a shaft coupling mode.

Further, the wing switch comprises a circular button, a return spring and a fixed column, the position of the lower end face of the circular button is fixedly connected with the fixed column, and the outer peripheral face of the fixed column is surrounded by the return spring.

Furthermore, the wing unfolding mechanism comprises wing extension columns, an inner-notch type circular fixing column, minor arc sliding blocks and an inner-notch type circular fixing column interface, the wing extension columns are arranged at four positions, every two positions are symmetrically arranged into a group, the two ends of one group, which are not connected with the lifting mechanism, are fixedly connected with the minor arc sliding blocks, the two minor arc sliding blocks are connected with the inner-notch type circular fixing column in a sliding mode, and the inner-notch type circular fixing column interface is arranged on one side of the upper end face of the inner-notch type circular fixing column.

Further, wing deployment mechanism is still including cylinder type fixed block interface, expanding spring, major arc sliding block and cylinder type fixed block, cylinder type fixed block interface has been seted up to cylinder type fixed block up end one side, expanding spring extends post one side with a set of wing, major arc sliding block sliding connection is in the outer peripheral face position of cylinder type fixed block.

The utility model discloses at least, include following beneficial effect:

because the lifting mechanism is arranged, the wings arranged in the wing balance weight can rotate at high speed through the rotating shaft to play a lifting role, because the wing switch is arranged, the circular button in the wing switch can carry out vertical linear motion on the fixed column fixedly connected with the lower end surface of the circular button through the return spring at the lower part, because the wing unfolding mechanism is arranged, wherein the wing extension column is arranged, the minor arc sliding blocks arranged at the two sides of the wing extension column can slide around the periphery of the inner segment type circular fixed column, the inner-notch type circular fixing column is designed to be provided with a semicircular groove inside, can be conveniently inserted and connected with the cylindrical fixing block, is convenient for the two groups of wing extension columns to be embedded, the inner-notch type circular fixing column connector is arranged on one side of the upper end surface of the inner-notch type fixing column, and the fixing column in the wing switch can be conveniently inserted into the inner-notch type circular fixing column connector for fixed connection.

Additional advantages, objects, and features of the invention will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the invention.

Drawings

Fig. 1 is a schematic side view of the present invention.

Fig. 2 is a schematic view of the structure of the present invention.

Fig. 3 is a schematic top view of the present invention.

Fig. 4 is a schematic view of the wing deployment structure of the present invention.

Fig. 5 is a schematic diagram of a partially enlarged structure at a in fig. 4 according to the present invention.

Fig. 6 is a schematic diagram of a partially enlarged structure at B in fig. 4 according to the present invention.

Fig. 7 is a schematic structural diagram of a wing deployment mechanism of the present invention.

In the drawings, the corresponding relationship between the component names and the reference numbers is as follows:

1. an unmanned aerial vehicle chassis; 2. a lifting mechanism; 201. an airfoil; 202. a wing counterbalance; 203. a rotating shaft; 3. a motion camera; 4. a wing switch; 401. a circular button; 402. a return spring; 403. fixing a column; 5. a wing deployment mechanism; 501. a wing extension post; 502. an inner-notch type round fixing column; 503. a minor arc slider; 504. an inner-opening type round fixed column interface; 505. a cylindrical fixed block interface; 506. a tension spring; 507. a major arc slider; 508. a cylindrical fixed block; 6. unmanned aerial vehicle supporting legs; 7. and extending the column groove.

Detailed Description

The following describes embodiments of the present invention in further detail with reference to the accompanying drawings and examples. The following examples are intended to illustrate the invention, but are not intended to limit the scope of the invention.

In the description of the present invention, "a plurality" means two or more unless otherwise specified; the terms "upper", "lower", "left", "right", "inner", "outer", "front", "rear", "head", "tail", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are merely for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like 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 "connected" and "connected" are to be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; may be directly connected or indirectly connected through an intermediate. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.

Example (b):

as shown in figures 1 to 7:

the utility model provides a foldable unmanned aerial vehicle's quick wing structure that expandes, including unmanned aerial vehicle machine case 1, motion camera 3, wing expansion mechanism 5, unmanned aerial vehicle landing leg 6 is equipped with everywhere altogether, and fixed connection is in 2 terminal surface positions in everywhere lifting mechanism, and 1 upper end surface central point of unmanned aerial vehicle machine case puts elastic connection has wing switch 4, and motion camera 3 sets up in 1 narrow limit one side position of unmanned aerial vehicle machine case, and wing expansion mechanism 5 is installed and is being extended post 7 insides.

The lifting mechanism 2 comprises a wing 201, a wing balance block 202 and a rotating shaft 203, wherein the wing balance block 202 is designed to be a square block, the wing 201 penetrates through the wing balance block 202, the wing balance block 202 is coupled to the upper end face of the rotating shaft 203, and the wing 201 fixed in the wing balance block 202 can rotate at a high speed through the rotating shaft 203 to play a lifting role.

The wing switch 4 comprises a round button 401, a return spring 402 and a fixing column 403, the fixing column 403 is fixedly connected to the lower end face of the round button 401, the return spring 402 surrounds the outer peripheral face of the fixing column 403, and the round button 401 in the wing switch 4 can perform vertical linear motion on the fixing column 403 fixedly connected to the lower end face of the round button 401 through the return spring 402 below the round button 401.

The wing unfolding mechanism 5 comprises a wing extending column 501, an inner-notch type circular fixing column 502, minor arc sliding blocks 503 and inner-notch type circular fixing column interfaces 504, the wing extending column 501 is provided with four positions, every two positions are symmetrically arranged into a group, the two ends of one group which are not connected with the lifting mechanism 2 are fixedly connected with the minor arc sliding blocks 503, the two minor arc sliding blocks 503 are connected with the inner-notch type circular fixing column 502 in a sliding mode, the inner-notch type circular fixing column interfaces 504 are arranged on one side of the upper end face of the inner-notch type circular fixing column 502, the wing extending column 501 and the minor arc sliding blocks 503 arranged on the two sides of the wing extending column 501 can slide around the periphery of the inner-notch type circular fixing column 502.

The wing unfolding mechanism 5 further comprises a cylindrical fixed block interface 505, an extension spring 506, a major arc sliding block 507 and a cylindrical fixed block 508, wherein the cylindrical fixed block interface 505 is arranged on one side of the upper end face of the cylindrical fixed block 508, the extension spring 506 is used for connecting one side of the wing extension columns 501, the major arc sliding block 507 is connected to the position of the outer peripheral face of the cylindrical fixed block 508 in a sliding mode, and the extension spring 506 is arranged for enabling the two wing extension columns 501 to be contracted and unfolded.

The specific use mode and function of the embodiment are as follows:

in the utility model, firstly, the unmanned aerial vehicle is placed at a proper position through the unmanned aerial vehicle supporting legs 6, then the return spring 402 is pressed by pressing the circular button 401 in the wing switch 4 at the central position of the surface of the upper end of the unmanned aerial vehicle case 1, the return spring 402 can drive the fixing column 403 fixedly connected with the bottom surface of the lower end of the circular button 401 to pop out, the segment type circular fixing column 502 and the cylindrical fixing block 508 in the wing unfolding mechanism 5 can be quickly unfolded along the stretching column groove 7 through the extension spring 506 connected with the outer sides of the two groups of wing stretching columns 501 after popping out, when the wings 201 need to be retracted, the two groups of wing extension columns 501 are directly pressed back into the extension column groove 7 and retracted back into the extension column groove 7, and pressing the round button 401 again, inserting the fixing column 403 into the through holes formed in the fixing column interface 504 and the cylindrical fixing block interface 505 through the return spring 402, and completing the wing retraction operation.

The embodiments of the present invention have been presented for purposes of illustration and description, and are not intended to be exhaustive or limited to the invention in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. The embodiment was chosen and described in order to best explain the principles of the invention and the practical application, and to enable others of ordinary skill in the art to understand the invention for various embodiments with various modifications as are suited to the particular use contemplated.

Claims

1. The utility model provides a foldable unmanned aerial vehicle's quick wing structure that expandes which characterized in that: including unmanned aerial vehicle machine case (1), motion camera (3), wing deployment mechanism (5), unmanned aerial vehicle landing leg (6): unmanned aerial vehicle landing leg (6) are equipped with everywhere altogether, and fixed connection is terminal surface position under lifting mechanism (2) everywhere respectively, unmanned aerial vehicle machine case (1) upper end surface central point puts elastic connection has wing switch (4), motion camera (3) set up in unmanned aerial vehicle machine case (1) narrow limit one side position, wing deployment mechanism (5) are installed inside extending post groove (7).

2. A folding drone's fast deployment wing structure as claimed in claim 1, characterised by: the lifting mechanism (2) comprises a wing (201), a wing balance block (202) and a rotating shaft (203), wherein the wing balance block (202) is designed to be a square block, the wing (201) penetrates through the wing balance block (202), and the wing balance block (202) is coupled to the upper end face of the rotating shaft (203).

3. A folding drone's fast deployment wing structure as claimed in claim 1, characterised by: the wing switch (4) comprises a round button (401), a return spring (402) and a fixed column (403), the fixed column (403) is fixedly connected to the lower end face of the round button (401), and the return spring (402) is arranged on the peripheral face of the fixed column (403) in a surrounding mode.

4. A folding drone's fast deployment wing structure as claimed in claim 1, characterised by: the wing unfolding mechanism (5) comprises wing extension columns (501), an inner-notch type circular fixing column (502), minor arc sliding blocks (503) and inner-notch type circular fixing column interfaces (504), the wing extension columns (501) are arranged at four positions, every two positions are symmetrically arranged into one group, the two ends of one group, which are not connected with the lifting mechanism (2), are fixedly connected with the minor arc sliding blocks (503), the two minor arc sliding blocks (503) are in sliding connection with the inner-notch type circular fixing column (502), and the inner-notch type circular fixing column interfaces (504) are arranged on one side of the upper end face of the inner-notch type circular fixing column (502); minor arc sliding blocks (503) arranged on two sides of the wing extension column (501) can slide around the periphery of the inner segment type circular fixing column (502).

5. The folding drone quick-deployment wing structure of claim 4, wherein: wing deployment mechanism (5) are still including cylinder type fixed block interface (505), expanding spring (506), major arc sliding block (507) and cylinder type fixed block (508), cylinder type fixed block interface (505) have been seted up to cylinder type fixed block (508) up end one side, expanding spring (506) extend post (501) one side with a set of wing, major arc sliding block (507) sliding connection is in the outer peripheral face position of cylinder type fixed block (508).