CN220076684U - Unmanned aerial vehicle fuselage skeleton based on die casting - Google Patents

Abstract

The utility model provides an unmanned aerial vehicle fuselage skeleton based on die casting, which comprises: end plate, two loading board and two curb plates. The bearing plate and the side plates are connected end to form a frame structure, and the end plates are arranged on the frame structure; the edge of each bearing plate is provided with a plurality of splicing hooks and a plurality of limiting convex blocks, the limiting convex blocks are provided with positioning grooves, the side plates are provided with inserts matched with the positioning grooves, the limiting convex blocks are abutted against the side plates, and the inserts are embedded into the positioning grooves; the splicing hooks are attached to the outer walls of the side plates, mounting holes are formed in the splicing hooks, and fixing holes are formed in the side plates. The fuselage skeleton is assembled by plates such as end plate, loading board and curb plate and forms, makes fuselage skeleton thickness further attenuate, is favorable to reducing fuselage skeleton quality to this reduces unmanned aerial vehicle flight and is the loss of electric energy, is equipped with spacing lug and splice hook assistance-localization real-time between each plate, improves the joint force between the plate, makes fuselage skeleton concatenation process simpler and more convenient, the structure is more firm.

Description

Unmanned aerial vehicle fuselage skeleton based on die casting

Technical Field

The utility model relates to the field of die casting, in particular to an unmanned aerial vehicle body framework based on die casting.

Background

The unmanned aerial vehicle is a small-sized aircraft controlled by wireless remote control equipment, and mainly comprises a fuselage skeleton, a control element arranged in the fuselage skeleton, a battery and wings.

The unmanned aerial vehicle comprises a frame, a frame and a frame, wherein the frame is a main bearing part on the unmanned aerial vehicle, and the frame is integrally formed by die casting of aluminum alloy. The fuselage skeleton manufactured in the mode can improve the assembly efficiency of the unmanned aerial vehicle, but also has larger mass, which means that the unmanned aerial vehicle needs to consume more electric quantity in the flight process, namely the sustainable flight time of the unmanned aerial vehicle is shortened.

Therefore, how to optimize the existing frame structure of the airframe, so that the airframe is lighter and more convenient is a problem to be solved.

Disclosure of Invention

The utility model aims to overcome the defects in the prior art, and provides an unmanned aerial vehicle body framework based on die casting, which is lighter and thinner in structure and beneficial to reducing the overall quality of an unmanned aerial vehicle.

The aim of the utility model is realized by the following technical scheme:

an unmanned aerial vehicle fuselage skeleton based on die casting, includes: the device comprises an end plate, two bearing plates and two side plates;

the bearing plates and the side plates are alternately distributed, the bearing plates and the side plates are connected end to form a frame structure with a rectangular cross section, and the end plates are arranged on the frame structure;

the edge of each bearing plate is provided with a plurality of splicing hooks and a plurality of limiting convex blocks, the limiting convex blocks are provided with positioning grooves, the side plates are provided with inserts matched with the positioning grooves, the limiting convex blocks are abutted against the side plates, and the inserts are embedded into the positioning grooves;

the splicing hooks are attached to the outer walls of the side plates, mounting holes are formed in the splicing hooks, and fixing holes matched with the mounting holes are formed in the side plates.

In one embodiment, the splice hook is located on a limit bump.

In one embodiment, the splice hooks and the limit bumps are alternately distributed along the edge of the carrier plate.

In one embodiment, the bearing plate, the side plate and the end plate are all provided with a plurality of hollow holes.

In one embodiment, the bearing plate, the side plate and the end plate are all provided with reinforcing ribs.

In one embodiment, the side plate is provided with an auxiliary positioning lug, and the auxiliary positioning lug is used for being attached to the outer wall of the bearing plate.

In one embodiment, the fixing hole is located on the auxiliary positioning protrusion.

In one embodiment, the length of the detent is greater than the length of the insert.

In one embodiment, an upright post is arranged at a position, attached to the splicing hook, on the side plate, and the fixing hole is located on the upright post.

In one embodiment, the quick-connection socket further comprises a quick-connection pin and a quick-connection socket, wherein the quick-connection socket is embedded in the upright post, two elastic baffle plates are arranged on the quick-connection socket, the two elastic baffle plates are arranged in opposite directions, and a clamping space is arranged between the two elastic baffle plates;

the quick connecting nails penetrate through the mounting holes and the fixing holes, a blocking portion and a transition portion are arranged on the quick connecting nails, the transition portion is conical, the diameter of the transition portion increases gradually from one side close to the blocking portion to one side far away from the blocking portion, and an avoidance groove is formed in the transition portion towards the position of the elastic blocking piece;

the width of the blocking part is larger than the clamping space, the thickness of the blocking part is smaller than the clamping space, and the tail end of the elastic blocking piece is used for being propped against the blocking part.

To sum up, the fuselage skeleton is assembled by plates such as end plate, loading board and curb plate and forms, makes fuselage skeleton thickness further attenuate, is favorable to reducing fuselage skeleton quality to this reduces unmanned aerial vehicle flight and is the loss of electric energy, is equipped with spacing lug and splice hook assistance-localization real-time between each plate, improves the joint force between the plate, makes fuselage skeleton concatenation process simpler and more convenient, the structure is more firm.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the drawings that are needed in the embodiments will be briefly described below, it being understood that the following drawings only illustrate some embodiments of the present utility model and therefore should not be considered as limiting the scope, and other related drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

Fig. 1 is a schematic structural view of a die-cast-based unmanned aerial vehicle fuselage skeleton;

fig. 2 is a schematic view of the die casting based unmanned aerial vehicle fuselage skeleton of fig. 1 from another perspective;

FIG. 3 is an exploded view of the die cast based unmanned aerial vehicle fuselage skeleton shown in FIG. 1;

FIG. 4 is a schematic view of the mating of the splice hook with the side panel;

FIG. 5 is a schematic view of a structure of a carrier plate;

FIG. 6 is a schematic diagram of a side plate structure;

FIG. 7 is a schematic view of the structure of the quick connect pin and the quick connect socket;

FIG. 8 is a schematic diagram of the mating of the quick connect pin, the quick connect socket, and the carrier plate and side plate;

FIG. 9 is a diagram (I) showing the mating state of the quick connect pin and the quick connect socket;

fig. 10 is a diagram (two) showing the mating state of the quick connect pin and the quick connect socket.

Reference numerals

Unmanned aerial vehicle fuselage skeleton 10, hollow hole 11, strengthening rib 12, end plate 100, loading board 200, splice hook 210, mounting hole 211, spacing lug 220, constant head tank 221, curb plate 300, insert 310, fixed orifices 320, auxiliary positioning lug 330, stand 340, T-shaped groove 341, quick connect nail 400, blocking part 410, transition part 420, dodge groove 421, quick connect socket 500, elastic baffle 510, clamping space 520 based on die casting;

Detailed Description

In order that the utility model may be readily understood, a more complete description of the utility model will be rendered by reference to the appended drawings. The drawings illustrate preferred embodiments of the utility model. This utility model may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete.

It will be understood that when an element is referred to as being "fixed to" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present. The terms "vertical," "horizontal," "left," "right," and the like are used herein for illustrative purposes only and are not meant to be the only embodiment.

Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this utility model belongs. The terminology used herein in the description of the utility model is for the purpose of describing particular embodiments only and is not intended to be limiting of the utility model. The term "and/or" as used herein includes any and all combinations of one or more of the associated listed items.

Referring to fig. 1 and 2, the present utility model provides an unmanned aerial vehicle fuselage skeleton 10 based on die casting, comprising: end plate 100, two carrier plates 200 and two side plates 300.

Referring to fig. 3, the end plate 100, the bearing plate 200 and the side plate 300 are all plate-shaped members formed by die casting of aluminum alloy, and divide the frame into a plurality of independent plates, so that the frame is thinner and lighter as a whole, and the energy consumption of the unmanned aerial vehicle during flight can be reduced.

The bearing plates 200 and the side plates 300 are alternately distributed, and the bearing plates 200 and the side plates 300 are connected end to form a frame structure with a rectangular cross section, and the end plates 100 are arranged on the frame structure. That is, the two bearing plates 200 are arranged opposite to each other, the two side plates 300 are arranged opposite to each other, and two sides of each bearing plate 200 are respectively connected with the two side plates 300, and the end plate 100 is covered at the opening of the frame structure.

Referring to fig. 2 and fig. 4, a plurality of splice hooks 210 and a plurality of limiting protrusions 220 are disposed on the edge of each carrier plate 200, and specifically, the splice hooks 210 are located on the limiting protrusions 220 (as shown in fig. 4), or may be directly located on the edge of the carrier plate 200, and when the splice hooks 210 are located on the edge of the carrier plate 200, the splice hooks 210 and the limiting protrusions 220 are alternately distributed along the edge of the carrier plate 200 (as shown in fig. 5).

Referring to fig. 4 and 5, the positioning groove 221 is formed on the limiting bump 220, the insert 310 (as shown in fig. 6) matching with the positioning groove 221 is disposed on the side plate 300, and when the carrier 200 is connected to the side plate 300, the limiting bump 220 abuts against the side plate 300, and the insert 310 is embedded into the positioning groove 221.

Referring to fig. 5 and 6, the splicing hook 210 is attached to an outer wall of the side plate 300, a mounting hole 211 is formed in the splicing hook 210, and a fixing hole 320 matching the mounting hole 211 is formed in the side plate 300.

The following describes the assembly principle of the unmanned aerial vehicle fuselage skeleton 10 based on die casting described above:

firstly, one of the bearing plates 200 is tiled on an assembly workbench;

aligning the long side of the side plate 300 with the long side of the bearing plate 200, turning the side plate 300 to enable the insert 310 to face the bearing plate 200, attaching the splicing hooks 210 to the outer wall of the side plate 300 when the side plate 300 is placed on the bearing plate 200, and hooking the side of the side plate 300, which is contacted with the bearing plate 200, by the splicing hooks 210 so that the edges of the bearing plate 200 and the side plate 300 are kept attached;

then, the side plate 300 is moved along the long side direction of the bearing plate 200, the insert 310 slides to the position of the positioning groove 221, pressure is applied to the side plate 300, the insert 310 is embedded into the positioning groove 221, at the moment, the side plate 300 is abutted against the limiting projection 220, the mounting hole 211 on the splicing hook 210 is aligned with the fixing hole 320 on the side plate 300, the screw penetrates through the mounting hole 211 and the fixing hole 320, and one side of the side plate 300 is spliced;

by adopting the splicing mode, the other bearing plate 200 is paved on the other side of the side plate 300, the connection between the bearing plate 200 and the side plate 300 is completed, and the two bearing plates 200 and the two side plates 300 enclose a frame-shaped structure with two open ends;

after the end plate 100 is covered on the frame structure, the frame of the machine body is assembled.

It can be known that, in the assembling process of the above-mentioned frame body, the splicing hooks 210, the limiting protrusions 220 and the inserts 310 are engaged between the side plates 300 and the carrying plates 200 to perform preliminary connection, and the screws are used for fastening, so that the problems of error and reverse assembly can be avoided, the alignment operation in the assembling process of the frame body can be saved, the assembling of the frame body is easier, and the splicing hooks 210 form a barrier on the outer walls of the side plates 300 after the assembling is completed, so that the side plates 300 are connected with the carrying plates 200, and the structural strength of the frame body is improved.

To sum up, the fuselage skeleton is assembled by plates such as end plate 100, loading board 200 and curb plate 300 and forms, makes fuselage skeleton thickness further attenuate, is favorable to reducing fuselage skeleton quality to this reduces unmanned aerial vehicle flight and is the loss of electric energy, is equipped with spacing lug 220 and splice hook 210 assistance-localization real-time between each plate, improves the joint force between the plate, makes fuselage skeleton concatenation process simpler and more convenient, the structure is more firm.

Referring to fig. 1, in order to further reduce the weight of the unmanned aerial vehicle body skeleton 10 based on die casting, a plurality of hollow holes 11 are formed on the carrier plate 200, the side plates 300 and the end plates 100, and the mass of the carrier plate 200, the side plates 300 and the end plates 100 is reduced through the hollow holes 11. And the bearing plate 200, the side plate 300 and the end plate 100 are all provided with reinforcing ribs 12.

Referring to fig. 4 and 6, in an embodiment, the side plate 300 is provided with an auxiliary positioning protrusion 330, and the auxiliary positioning protrusion 330 is attached to the outer wall of the carrier 200. The auxiliary positioning protruding blocks 330 are used for blocking the side plates 300 from deviating towards the inner cavity of the unmanned aerial vehicle body frame 10 based on die casting, and improving the structural stability of the unmanned aerial vehicle body frame 10 based on die casting.

In one embodiment, the length of the locating slot 221 is greater than the length of the insert 310.

Referring to fig. 8, in one embodiment, a post 340 is disposed on the side plate 300 at a position where the splice hook 210 is attached, and the fixing hole 320 is located on the post 340. The side plate 300 has a plate-shaped structure, and has a small thickness, and effective threads are short after the threaded holes are formed, and the thickness of the position where the side plate 300 is matched with the screw is increased by arranging the upright post 340 so as to ensure the connection strength.

Above-mentioned unmanned aerial vehicle fuselage skeleton 10 based on die casting is formed by a plurality of plates concatenation, needs to have a plurality of threaded connection positions between each plate, and it is long to beat screw occupation time in the process of assembling, leads to the inefficiency of assembling of unmanned aerial vehicle fuselage skeleton 10 based on die casting. To solve the above problems, the unmanned aerial vehicle fuselage skeleton 10 based on die casting further includes a quick connect pin 400 and a quick connect socket 500.

Referring to fig. 7 and 8, the quick connector 500 is embedded in the upright 340, and specifically, the upright 340 is provided with a T-shaped slot 341, and the quick connector 500 is accommodated in the T-shaped slot 341.

Referring to fig. 7, two elastic blocking pieces 510 are disposed on the quick connector 500, the two elastic blocking pieces 510 are disposed opposite to each other, and a clamping space 520 is disposed between the two elastic blocking pieces 510;

referring to fig. 7 and 8, the quick connect pin 400 is provided with a mounting hole 211 and a fixing hole 320, the quick connect pin 400 is provided with a blocking portion 410 and a transition portion 420, the transition portion 420 is cone-shaped, the thickness of the transition portion 420 increases from one side close to the blocking portion 410 to one side far from the blocking portion 410, and the position of the transition portion 420 facing the elastic baffle plate 510 is provided with an avoidance groove 421;

the width of the blocking portion 410 is greater than the clamping space 520, the thickness of the blocking portion 410 is smaller than the clamping space 520, and the end of the elastic blocking piece 510 is used for abutting against the blocking portion 410. I.e., the wide side of the blocking portion 410 cannot pass through the clamping space 520, and the narrow side of the blocking portion 410 can pass through the clamping space 520.

Referring to fig. 8, specifically, when the carrier board 200 and the side board 300 are spliced, the quick-connect socket 500 is embedded in the T-shaped groove 341;

when the quick-connect pin 400 passes through the mounting hole 211 and the fixing hole 320 and the quick-connect pin 400 enters the fixing hole 320, the blocking part 410 stretches into the clamping space 520 between the two elastic blocking pieces 510, and if the narrow edge of the blocking part 410 is aligned with the clamping space 520 at this time, the blocking part 410 smoothly passes through between the two elastic blocking pieces 510; otherwise, the two elastic blocking pieces 510 block the blocking portion 410, and the quick connect pin 400 is rotated until the narrow sides of the blocking portion 410 are aligned with the clamping space 520;

after the blocking portion 410 passes through the clamping space 520, the transition portion 420 reaches the position where the two elastic blocking pieces 510 are located, and because the transition portion 420 is conical, the transition portion 420 can prop open the two elastic blocking pieces 510 when the quick-connect pin 400 penetrates into the fixing hole 320;

when the nut of the quick-connect pin 400 is attached to the carrier plate 200, the threading operation of the quick-connect pin 400 is stopped, the mating state of the quick-connect pin 400 and the quick-connect socket 500 is shown in fig. 10, and the avoiding groove 421 is staggered with the elastic baffle 510;

the quick connect pin 400 is rotated by 90 ° to make the avoiding groove 421 on the transition portion 420 face the elastic baffle plate 510, the elastic baffle plate 510 are mutually gathered, and because the quick connect pin 400 is rotated, the tail end of the elastic baffle plate 510 faces the broadside of the blocking portion 410, as shown in fig. 9, the blocking portion 410 is blocked by the elastic baffle plate 510, that is, the quick connect pin 400 cannot be pulled out from the quick connect socket 500 in this state, and a clamping force is applied to the bearing plate 200 and the side plate 300 through the cooperation of the quick connect pin 400 and the quick connect socket 500, so that the bearing plate 200 and the side plate 300 are combined together instead of screws. Only need rotate 90 in the grafting process, can effectively improve the packaging efficiency of unmanned aerial vehicle fuselage skeleton 10 of die-casting.

The above examples illustrate only a few embodiments of the utility model, which are described in detail and are not to be construed as limiting the scope of the utility model. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the utility model, which are all within the scope of the utility model. Accordingly, the scope of protection of the present utility model is to be determined by the appended claims.

Claims (10)

1. Unmanned aerial vehicle fuselage skeleton based on die casting, its characterized in that includes: the device comprises an end plate, two bearing plates and two side plates;

the bearing plates and the side plates are alternately distributed, the bearing plates and the side plates are connected end to form a frame structure with a rectangular cross section, and the end plates are arranged on the frame structure;

the edge of each bearing plate is provided with a plurality of splicing hooks and a plurality of limiting convex blocks, the limiting convex blocks are provided with positioning grooves, the side plates are provided with inserts matched with the positioning grooves, the limiting convex blocks are abutted against the side plates, and the inserts are embedded into the positioning grooves;

the splicing hooks are attached to the outer walls of the side plates, mounting holes are formed in the splicing hooks, and fixing holes matched with the mounting holes are formed in the side plates.

2. The die cast based unmanned aerial vehicle fuselage skeleton of claim 1, wherein the splice hooks are located on limit bumps.

3. The die cast based unmanned aerial vehicle fuselage skeleton of claim 1, wherein the splice hooks alternate with the limit bumps along the edges of the carrier plate.

4. The die casting-based unmanned aerial vehicle fuselage skeleton of claim 1, wherein the bearing plate, the side plates and the end plates are provided with a plurality of hollowed holes.

5. The die-cast-based unmanned aerial vehicle fuselage skeleton of claim 1, wherein the carrier plate, the side plates and the end plates are provided with reinforcing ribs.

6. The die-casting-based unmanned aerial vehicle fuselage skeleton according to claim 1, wherein the side plates are provided with auxiliary positioning lugs, and the auxiliary positioning lugs are used for being attached to the outer walls of the bearing plates.

7. The die cast based unmanned aerial vehicle fuselage skeleton of claim 6, wherein the securing holes are located on the auxiliary locating protrusions.

8. The die cast based unmanned aerial vehicle fuselage skeleton of claim 1, wherein the length of the locating slot is greater than the length of the insert.

9. The die-casting-based unmanned aerial vehicle fuselage skeleton according to claim 1, wherein a column is arranged at a position on the side plate, which is attached to the splicing hooks, and the fixing holes are formed in the column.

10. The unmanned aerial vehicle fuselage skeleton based on die casting of claim 9, further comprising a quick-connect pin and a quick-connect socket, wherein the quick-connect socket is embedded in the upright post, two elastic blocking pieces are arranged on the quick-connect socket, the two elastic blocking pieces are arranged in opposite directions, and a clamping space is arranged between the two elastic blocking pieces;

the quick connecting nails penetrate through the mounting holes and the fixing holes, a blocking portion and a transition portion are arranged on the quick connecting nails, the transition portion is conical, the diameter of the transition portion increases gradually from one side close to the blocking portion to one side far away from the blocking portion, and an avoidance groove is formed in the transition portion towards the position of the elastic blocking piece;

the width of the blocking part is larger than the clamping space, the thickness of the blocking part is smaller than the clamping space, and the tail end of the elastic blocking piece is used for being propped against the blocking part.