CN214875522U

CN214875522U - Unmanned aerial vehicle wing convenient to installation

Info

Publication number: CN214875522U
Application number: CN202121812650.8U
Authority: CN
Inventors: 柯宗泽; 吴宽
Original assignee: Guangzhou Jizhi High Tech Co ltd
Current assignee: Guangzhou Jizhi High Tech Co ltd
Priority date: 2021-08-05
Filing date: 2021-08-05
Publication date: 2021-11-26
Anticipated expiration: 2031-08-05

Abstract

The utility model relates to an unmanned air vehicle technique field just discloses an unmanned aerial vehicle wing convenient to installation, the reciprocating impact tunnel drilling machine comprises a machine body, the mounting groove has all been seted up to the left and right sides of fuselage. This unmanned aerial vehicle wing convenient to installation, drive the connecting rod downstream through pulling the handle downwards, the connecting rod drives slider downstream extrusion reset spring, until the handle extends to the below of fuselage completely, it is rotatory that the handle passes through the slider drive dwang this moment to rotate, and then it is rotatory with the pivot to drive driven bevel gear through drive bevel gear, the pivot can constantly twine the haulage rope in its outside at rotatory in-process, and then drive both sides dog back of the body removal from the other side about driving, thereby income the inside to the spacing groove with the stopper, extend the inside to the mounting groove with the wing this moment, then loosen the handle, can drive the inside that the stopper extends to the draw-in groove under spacing spring's spring action, thereby restrict the position to the wing, the mesh of being convenient for install the wing has been realized.

Description

Unmanned aerial vehicle wing convenient to installation

Technical Field

The utility model relates to an unmanned air vehicle technique field specifically is an unmanned aerial vehicle wing convenient to installation.

Background

The unmanned plane is called unmanned plane for short, is an unmanned plane operated by radio remote control equipment and a self-contained program control device, has no cockpit on the plane, but is provided with an automatic pilot, a program control device and other equipment, and personnel on the ground, a naval vessel or a mother aircraft remote control station pass through radar and other equipment, the system can be tracked, positioned, remotely controlled, remotely measured and digitally transmitted, can take off like a common airplane under the radio remote control or be launched and lifted off by a boosting rocket, and can also be carried to the air by a mother aircraft for throwing flight and recovering, can land automatically in the same way as the landing process of a common airplane, can also be recovered by a remote control parachute or a barrier net, the unmanned aerial vehicle can be repeatedly used for many times, and is widely applied to aerial reconnaissance, monitoring, communication, anti-diving, electronic interference and the like.

But the wing of current unmanned aerial vehicle carries out fixed connection through the bolt mostly, leads to the convenience relatively poor, is unfavorable for the installation, so provides the unmanned aerial vehicle wing of being convenient for the installation.

SUMMERY OF THE UTILITY MODEL

Technical problem to be solved

The utility model provides a not enough to prior art, the utility model provides an unmanned aerial vehicle wing convenient to installation possesses the advantage such as being convenient for install the wing, and the wing of having solved current unmanned aerial vehicle is mostly all to carry out fixed connection through the bolt, leads to the convenience relatively poor, is unfavorable for the problem of installation.

(II) technical scheme

In order to realize the above-mentioned purpose of being convenient for install the wing, the utility model provides a following technical scheme: an unmanned aerial vehicle wing convenient to install comprises a body, wherein mounting grooves are formed in the left side and the right side of the body, wings with one ends extending to the outside are movably mounted in the mounting grooves, two mounting cavities which are positioned on the opposite sides of the two mounting grooves are formed in the body, the inner walls of the two opposite sides of the mounting cavities are communicated with two limiting grooves which are formed in the body and are respectively positioned on the upper side and the lower side of the mounting groove, a limiting block with one end extending to the inside of the wing is movably mounted in the limiting groove, a limiting rod with one end fixedly connected with the inner wall of the limiting groove on the side far away from the mounting groove is movably mounted in the limiting block, a limiting spring with one end fixedly connected with the inner wall of the limiting groove and sleeved on the outer side of the limiting rod is fixedly mounted on the side far away from the mounting groove of the limiting block, a rotating shaft is movably arranged between the left side and the right side of the inner wall of the mounting cavity, a driven bevel gear is fixedly arranged on the outer side of the rotating shaft, first pulleys positioned at the opposite sides of the limiting rods on the left side and the right side are fixedly arranged on the inner walls on the opposite sides of the limiting grooves on the upper side and the lower side, second pulleys which are respectively positioned on the upper side and the lower side of the rotating shaft are fixedly arranged on the inner walls on the opposite sides of the limiting grooves on the upper side and the lower side, two traction ropes which are respectively positioned on the upper side and the lower side of the rotating shaft and have one ends respectively penetrating through the second pulleys on the upper side and the lower side and the first pulleys and are fixedly connected with a stop block are wound on the outer sides of the two rotating shafts, two accommodating grooves which are respectively positioned below the two mounting cavities are arranged on the bottom of the machine body, a rotating rod with one end extending to the inside the mounting cavity is movably arranged on the inner top wall of the accommodating grooves, and a driving bevel gear meshed with the driven bevel gear is fixedly arranged on the top of the rotating rod, the inside of dwang has been seted up and has been accomodate the chamber, slidable mounting has the slider between the inner wall left and right sides in accomodating the chamber, the bottom fixed mounting of slider has the connecting rod that one end extends to the dwang bottom, fixed mounting has the reset spring of cover in the connecting rod outside between the bottom of slider and the interior diapire in accomodating the chamber.

Preferably, the upper side and the lower side of one end, located in the mounting groove, of the wing are provided with clamping grooves, and the clamping grooves are matched with the limiting blocks.

Preferably, the inside of stopper is cavity and its inner wall of keeping away from mounting groove one side is the opening, the inner wall of stopper is smooth design.

Preferably, the bearing is fixedly mounted on the left side and the right side of the inner wall of the mounting cavity, and the rotating shaft is rotatably connected with the mounting cavity through the bearing.

Preferably, the left side and the right side of the inner wall of the containing cavity are communicated with sliding grooves formed in the rotating rod, and the left side and the right side of the sliding block extend to the left side and the right side of the sliding groove respectively.

Preferably, the bottom fixed mounting of connecting rod has the handle that is located to accomodate the inslot portion, the inner diapire intercommunication of accomodating the chamber has the through-hole of seting up on the dwang and with connecting rod looks adaptation.

(III) advantageous effects

Compared with the prior art, the utility model provides an unmanned aerial vehicle wing convenient to installation possesses following beneficial effect:

this unmanned aerial vehicle wing convenient to installation, drive the connecting rod downstream through pulling the handle downwards, the connecting rod drives slider downstream extrusion reset spring, until the handle extends to the below of fuselage completely, it is rotatory that the handle passes through the slider drive dwang this moment to rotate, and then it is rotatory with the pivot to drive driven bevel gear through drive bevel gear, the pivot can constantly twine the haulage rope in its outside at rotatory in-process, and then drive both sides dog back of the body removal from the other side, thereby income stopper to the inside of spacing groove, extend the inside of wing to the mounting groove this moment, then loosen the handle, under spacing spring's spring action, can drive the inside that the stopper extends to the draw-in groove, thereby restrict the position to the wing, the mesh of being convenient for install the wing has been realized.

Drawings

FIG. 1 is a schematic structural view of the present invention;

fig. 2 is an enlarged view of a portion a in fig. 1 according to the present invention.

In the figure: the airplane comprises a fuselage 1, a mounting groove 2, wings 3, a mounting cavity 4, a limiting groove 5, a limiting block 6, a limiting rod 7, a stop block 8, a limiting spring 9, a rotating shaft 10, a driven bevel gear 11, a first pulley 12, a second pulley 13, a traction rope 14, a storage groove 15, a rotating rod 16, a driving bevel gear 17, a storage cavity 18, a sliding block 19, a connecting rod 20 and a return spring 21.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. 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.

Referring to fig. 1-2, the present invention provides a technical solution: an unmanned aerial vehicle wing convenient to install comprises a body 1, wherein the left side and the right side of the body 1 are both provided with mounting grooves 2, wings 3 with one ends extending to the outside are movably mounted in the mounting grooves 2, two mounting cavities 4 are formed in the body 1 and are positioned at the opposite sides of the two mounting grooves 2, the inner walls at the opposite sides of the two mounting cavities 4 are both communicated with two limiting grooves 5 which are formed in the body 1 and are respectively positioned at the upper side and the lower side of the mounting groove 2, limiting blocks 6 with one ends extending to the inside of the wings 3 are movably mounted in the limiting grooves 5, clamping grooves are formed in the upper side and the lower side of the wing 3 at the end positioned in the mounting groove 2, the clamping grooves are matched with the limiting blocks 6, the inside of the limiting blocks 6 is hollow, the inner wall of one side, far away from the mounting groove 2, of the limiting blocks 6 is provided with an opening, the inner wall of the limiting blocks 6 is of a smooth design, a limiting rod 7 with one end fixedly connected with the inner wall of one side, far away from the mounting groove 2, of the limiting groove 5, a stop block 8 positioned in the limiting groove 5 is fixedly arranged on the outer side of the limiting block 6, a limiting spring 9 with one end fixedly connected with the inner wall of the limiting groove 5 and sleeved on the outer side of the limiting rod 7 is fixedly arranged on one side of the stop block 8 far away from the mounting groove 2, a rotating shaft 10 is movably arranged between the left side and the right side of the inner wall of the mounting cavity 4, bearings are fixedly arranged on the left side and the right side of the inner wall of the mounting cavity 4, the rotating shaft 10 is rotatably connected with the mounting cavity 4 through the bearings, a driven bevel gear 11 is fixedly arranged on the outer side of the rotating shaft 10, first pulleys 12 positioned on the opposite sides of the limiting rods 7 on the left side and the right side are fixedly arranged on the inner walls on the opposite sides of the limiting grooves 5 on the upper side and the lower side respectively, two second pulleys 13 which are respectively positioned on the upper side and the lower side of the rotating shaft 10 are fixedly arranged on the inner walls on the opposite sides of the two mounting cavities 4, and a traction rope 14 with one end respectively passing through the second pulleys 13 on the upper side and the first pulleys 12 on the lower side and fixedly connected with the stop block 8 is wound on the outer side of the outer sides of the two rotating shafts 10, the bottom of the machine body 1 is provided with two accommodating grooves 15 which are respectively positioned below the two installation cavities 4, the inner top wall of each accommodating groove 15 is movably provided with a rotating rod 16, one end of each rotating rod 16 extends into the installation cavity 4, the top of each rotating rod 16 is fixedly provided with a driving bevel gear 17 meshed with the driven bevel gear 11, the inside of each rotating rod 16 is provided with an accommodating cavity 18, a sliding block 19 is arranged between the left side and the right side of the inner wall of each accommodating cavity 18 in a sliding manner, the left side and the right side of the inner wall of each accommodating cavity 18 are both communicated with sliding grooves formed in the corresponding rotating rod 16, the left side and the right side of each sliding block 19 respectively extend into the left sliding groove and the right sliding groove, the bottom of each sliding block 19 is fixedly provided with a connecting rod 20, the bottom of each connecting rod 20 is fixedly provided with a handle positioned in the corresponding accommodating groove 15, the inner bottom wall of each accommodating cavity 18 is communicated with through holes formed in the corresponding to the corresponding connecting rod 20, a return spring 21 sleeved outside the connecting rod 20 is fixedly installed between the bottom of the sliding block 19 and the inner bottom wall of the accommodating cavity 18.

In conclusion, according to the wing of the unmanned aerial vehicle convenient to install, the connecting rod 20 is driven to move downwards by pulling the handle downwards, the connecting rod 20 drives the sliding block 19 to move downwards to extrude the return spring 21 until the handle extends to the lower part of the body 1 completely, at the moment, the rotating handle drives the rotating rod 16 to rotate through the sliding block 19, the driven bevel gear 11 and the rotating shaft 10 are driven to rotate by driving the bevel gear 17, the rotating shaft 10 continuously winds the traction rope 14 on the outer side of the rotating shaft in the rotating process, the upper side stop block 8 and the lower side stop block 8 are driven to move back to back, the limit block 6 is taken in the limit groove 5, the wing 3 extends to the inside of the mounting groove 2, then the handle is loosened, the limit block 6 is driven to extend to the inside of the clamping groove under the elastic force of the limit spring 9, the position of the wing 3 is limited, and the purpose of facilitating the installation of the wing is achieved, the problem of current unmanned aerial vehicle's wing mostly all carry out fixed connection through the bolt, lead to the convenience relatively poor, be unfavorable for the installation is solved.

It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.

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. The utility model provides an unmanned aerial vehicle wing convenient to installation, includes fuselage (1), its characterized in that: the mounting groove is formed in each of the left side and the right side of the body (1), the mounting grooves (2) are formed in the mounting grooves (2), wings (3) with one ends extending to the outside of the mounting grooves are movably mounted in the body (1), two mounting cavities (4) are formed in the body (1) and located on the opposite sides of the two mounting grooves (2), limiting grooves (5) which are formed in the body (1) and located on the upper side and the lower side of the mounting grooves (2) respectively are communicated with the inner walls on the opposite sides of the two mounting cavities (4), limiting blocks (6) with one ends extending to the inside of the wings (3) are movably mounted in the limiting grooves (5), limiting rods (7) with one ends fixedly connected with the inner walls on one side of the mounting grooves (2) away from the limiting grooves (5) are movably mounted in the limiting grooves (6), stop blocks (8) located in the limiting grooves (5) are fixedly mounted on the outer sides of the limiting blocks (6), one side of the stop block (8) far away from the mounting groove (2) is fixedly provided with a limiting spring (9) with one end fixedly connected with the inner wall of the limiting groove (5) and sleeved on the outer side of the limiting rod (7), a rotating shaft (10) is movably mounted between the left side and the right side of the inner wall of the mounting cavity (4), the outer side of the rotating shaft (10) is fixedly provided with a driven bevel gear (11), the inner walls on the back sides of the limiting groove (5) on the upper side and the lower side are fixedly provided with first pulleys (12) positioned on the opposite sides of the limiting rod (7) on the left side and the right side respectively, the inner walls on the back sides of the two mounting cavities (4) are fixedly provided with two second pulleys (13) which are respectively positioned on the upper side and the lower side of the rotating shaft (10), the outer sides of the two rotating shafts (10) are respectively wound with two traction ropes (14) with one ends respectively penetrating through the second pulleys (13) on the upper side and the first pulleys (12) on the lower side and fixedly connected with the stop block (8), the bottom of fuselage (1) is seted up quantity and is two and is located two grooves (15) of accomodating of installation cavity (4) below respectively, the interior roof movable mounting who accomodates groove (15) has one end to extend to the inside dwang (16) of installation cavity (4), the top fixed mounting of dwang (16) has drive bevel gear (17) with driven bevel gear (11) meshing, the inside of dwang (16) has been seted up and has been accomodate chamber (18), slidable mounting has slider (19) between the inner wall left and right sides of accomodating chamber (18), the bottom fixed mounting of slider (19) has connecting rod (20) that one end extends to dwang (16) bottom, fixed mounting has reset spring (21) of cover in the connecting rod (20) outside between the bottom of slider (19) and the interior diapire of accomodating chamber (18).

2. A readily installable wing for a drone, according to claim 1, wherein: the wing (3) is located the upper and lower both sides of the inside one end of mounting groove (2) and has all seted up the draw-in groove, draw-in groove and stopper (6) looks adaptation.

3. A readily installable wing for a drone, according to claim 1, wherein: the inner part of the limiting block (6) is hollow, the inner wall of one side, away from the mounting groove (2), of the limiting block is an opening, and the inner wall of the limiting block (6) is designed to be smooth.

4. A readily installable wing for a drone, according to claim 1, wherein: the equal fixed mounting in inner wall left and right sides of installation cavity (4) has the bearing, pivot (10) are connected with installation cavity (4) rotation through the bearing.

5. A readily installable wing for a drone, according to claim 1, wherein: the inner wall left and right sides of accomodating chamber (18) all communicates and has seted up the spout on dwang (16), the left and right sides of slider (19) extends to the inside of controlling two spouts respectively.

6. A readily installable wing for a drone, according to claim 1, wherein: the bottom fixed mounting of connecting rod (20) has the handle that is located to accomodate inside groove (15), the interior diapire intercommunication of accomodating chamber (18) has the through-hole of seting up on dwang (16) and with connecting rod (20) looks adaptation.