CN113120255B

CN113120255B - Full quick-witted assembly fixture of integral type

Info

Publication number: CN113120255B
Application number: CN202110483143.2A
Authority: CN
Inventors: 赵颖; 邓军; 石章虎; 陈雪梅
Original assignee: Chengdu Aircraft Industrial Group Co Ltd
Current assignee: Chengdu Aircraft Industrial Group Co Ltd
Priority date: 2021-04-30
Filing date: 2021-04-30
Publication date: 2022-01-25
Anticipated expiration: 2041-04-30
Also published as: CN113120255A

Abstract

The invention discloses an integrated full-machine assembly tool which comprises a framework assembly, wherein a nose cone positioning assembly, a front landing frame assembly, a clamping plate positioning assembly, a drilling template assembly, a wing assembly, a heat dissipation barrel assembly and a frame beam positioning assembly are arranged on the framework assembly, the nose cone positioning assembly is arranged at the foremost end of the framework assembly, the front landing frame assembly is arranged behind the nose cone positioning assembly, the drilling template assembly is distributed in the middle of the framework assembly, the wing assembly is distributed on two sides of the framework assembly, the heat dissipation barrel assembly is arranged behind the framework assembly, and the clamping plate positioning assembly and the frame beam positioning assembly are both distributed on the upper portion of the framework assembly. The invention adopts the technologies of modularization, detachable parts, quick tool resetting and the like at multiple places, integrates the procedures of whole body assembly, involution, finish machining and the like of the airplane on a set of tool platform, ensures the requirements of high performance and short development period of the novel series of unmanned aerial vehicles, improves the corresponding speed of the tool and saves the manufacturing cost.

Description

Full quick-witted assembly fixture of integral type

Technical Field

The invention relates to the technical field of unmanned aerial vehicle assembly tools, in particular to an integrated full-machine assembly tool.

Background

The production of the unmanned aerial vehicle shows the characteristics of multiple varieties, small batch, frequent change and the like. Compared with the traditional model, the unmanned aerial vehicle development shows that the development period is very short, and the upgrading and updating speeds are also fast, so that great challenges are provided for the traditional development mode. For adapting to the development needs of novel small and medium-sized unmanned aerial vehicles, an unmanned aerial vehicle assembly integrated tool needs to be provided, so that the unmanned aerial vehicle front body, the middle body, the rear body, the wings are assembled, the assembly and the finish machining are integrated into the same tool for execution, the requirements of high performance and short development period of a novel series of unmanned aerial vehicles are ensured, meanwhile, the tool cost is greatly reduced, the quality and the competitiveness of the unmanned aerial vehicles are improved, and no relevant report aiming at the whole-machine assembly tool of the unmanned aerial vehicles exists at present.

Disclosure of Invention

The invention aims to provide an integrated full-machine assembly tool which integrates all assembly work of a front machine body, a middle machine body and a rear machine body of an airplane into one set of tool, saves space and field to the maximum extent, avoids repeated positioning work at multiple positions in the involution process of the machine bodies and improves assembly efficiency.

The invention is realized by the following technical scheme: the utility model provides a full quick-witted assembly fixture of integral type, includes the skeleton subassembly, install first awl locating component, preceding landing frame group price, cardboard locating component, jig plate subassembly, wing subassembly, heat dissipation section of thick bamboo subassembly, frame roof beam locating component on the skeleton subassembly, first awl locating component arranges the foremost of skeleton subassembly in, first awl locating component rear is arranged in to preceding landing frame group price, jig plate subassembly distributes in skeleton subassembly middle part, the wing subassembly distributes in skeleton subassembly both sides, heat dissipation section of thick bamboo subassembly, frame roof beam locating component arranges the rear portion of skeleton subassembly in, cardboard locating component and frame roof beam locating component all arrange on skeleton subassembly upper portion.

The working principle of the technical scheme is that a full-airplane integrated assembly mode is adopted, all assembly work of the front airplane body, the middle airplane body and the rear airplane body of the airplane is concentrated on one set of tooling, space and field are saved to the maximum extent, multiple repeated positioning work is saved, involution operation of all parts is avoided, the assembly period is greatly shortened, and the manufacturing efficiency is improved.

In order to better realize the invention, further, the framework component mainly comprises a framework main body, a corner support and foundation bolts; the framework main body is a giant frame consisting of a plurality of square steels and steel plates, the square steels are connected with each other, and a plurality of foundation bolts are arranged at the lower part of the framework main body.

In order to better realize the invention, the nose cone positioning component mainly comprises a stand column, a double-guide-rod positioner, a nose cone clamping plate, a frame positioning plate, a bolt, an end surface clamping plate, a web stringer positioner and a connecting support; the nose cone clamping plate is formed by welding four clamping plates into a cross shape, and the shape of each clamping plate is consistent with that of the nose cone of the airplane; the double-guide-rod positioner moves linearly along the direction of the guide rod to push the nose cone clamping plate to tightly press the nose cone of the airplane for positioning; the frame positioning plate and the end face clamping plate position and fix the airplane frame through the positioning pins and the web stringer positioner.

In order to better realize the invention, the front landing frame assembly mainly comprises a cross beam, a stop block and a bolt; the crossbeam is fixed in skeleton subassembly top, the dog is fixed to be set up in the crossbeam middle part, is provided with a plurality of bolts on the dog.

In order to better realize the invention, the clamping plate positioning component mainly comprises a front machine body clamping plate, a middle machine body clamping plate, a rear machine body clamping plate and a rear machine body back clamping plate, wherein the front machine body clamping plate, the middle machine body clamping plate, the rear machine body clamping plate and the rear machine body back clamping plate can position and assemble the frame beam of the airplane body, and each clamping plate is fed through a spiral positioner to compress and fix the additional frame of the airplane.

In order to better realize the invention, the drill plate assembly mainly comprises a plurality of supports and a plurality of drill plates, wherein the drill plates are arranged on the supports, bushings for drilling positioning holes on the machine body are arranged in the drill plates, and the supports are fixedly connected with the framework assembly through bolts.

In order to better realize the invention, the wing assembly mainly comprises a locking device and an adjustable supporting rod, wherein the locking device can position and fix the wings of the airplane, and the adjustable supporting rod can adjust the posture of the wings of the airplane to participate in the involution assembly of the wings and the airplane body.

In order to better realize the invention, the locking device mainly comprises a screw, a tangential compactor, an upper pressure plate, a spring, a T-shaped key, a lower pressure plate, a hand wheel, a nut, a spiral positioner and a welding support; the upper pressing plate is compressed and pressed in a tangential direction and is fixed on the screw rod; the lower pressing plate is positioned on the screw rod through a T-shaped key, the lower pressing plate is driven to axially move by rotating the hand wheel, and the nut is screwed to perform self-locking after the lower pressing plate is in place; the spring is used for axially compressing and positioning the upper pressing plate and the lower pressing plate; the integral mechanism of the spiral positioner axially moves and positions.

In order to better realize the invention, the adjustable supporting rod mainly comprises a riding wheel, a positioner and a welding support; a layer of felt is adhered to the surface of the riding wheel, the felt is in direct contact with an airplane body and can be adjusted up and down under the action of a positioner, and the airplane body can move back and forth by rolling on the riding wheel, so that the posture of a product is adjusted.

Compared with the prior art, the invention has the following advantages and beneficial effects:

(1) by the unmanned aerial vehicle assembly integrated tool, the assembly, the involution and the finish machining of the front body, the middle body, the rear body and the wings of the unmanned aerial vehicle are integrated into the same tool for execution, and the requirements of high performance and short development period of a novel series of unmanned aerial vehicles are met;

(2) according to the unmanned aerial vehicle assembly integrated tool, the space and the field are saved to the maximum extent, repeated positioning work at multiple positions in the closing process of the machine body is avoided, and the assembly efficiency is improved;

(3) according to the unmanned aerial vehicle assembly integrated tool, the technologies of modularization, detachable parts, quick tool reset and the like are adopted at multiple positions, the processes of whole body assembly, involution, finish machining and the like of an airplane are integrated on one tool platform, the corresponding speed of the tool is improved, the tool cost is greatly reduced, the outstanding contribution is made to the improvement of the quality and the competitiveness of the unmanned aerial vehicle, and the unmanned aerial vehicle assembly integrated tool is suitable for wide popularization and application.

Drawings

Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:

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

FIG. 2 is a perspective view of a frame assembly according to the present invention;

FIG. 3 is a perspective view of the nose cone positioning assembly of the present invention;

FIG. 4 is a perspective view of another view of the nose cone positioning assembly of the present invention;

FIG. 5 is a perspective view of the front landing gear assembly of the present invention;

FIG. 6 is a perspective view of the positioning assembly of the clamping plate of the present invention;

FIG. 7 is a perspective view of a drill plate assembly of the present invention;

FIG. 8 is a perspective view of a wing assembly of the present invention;

FIG. 9 is a perspective view of the clasping device of the present invention;

fig. 10 is a perspective view of the adjustable support rod of the present invention.

Wherein: 1-framework component, 2-nose cone positioning component, 3-front landing frame component, 4-clamping plate positioning component, 5-drilling template component, 6-wing component, 7-heat dissipation barrel component, 8-other frame beam positioning component, 11-framework main body, 12-corner support, 13-foundation bolt, 21-upright post, 22-double-guide-rod positioner, 23-nose cone clamping plate, 24-frame positioning plate, 25-positioning pin, 26-end-face clamping plate, 27-web stringer positioner, 28-connecting support, 31-cross beam, 32-stop block, 33-bolt, 41-front-body clamping plate, 42-middle-body clamping plate, 43-rear-body clamping plate, 44-rear-body back clamping plate, 51-support, 52-drilling template, 61-fastener, 62-adjustable support rod, 611-screw rod, 612-tangential compressor, 613-upper pressure plate, 614-spring, 615-T-shaped key, 616-lower pressure plate, 617-hand wheel, 618-nut, 619-spiral positioner, 620-welding support, 621-riding wheel, 622-positioner and 623-welding support.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention, and are not to be construed as limiting the present invention.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

Example 1:

the main structure of this embodiment, as shown in fig. 1, includes skeleton subassembly 1, install nose cone locating component 2, preceding landing frame group price 3, cardboard locating component 4, jig plate subassembly 5, wing subassembly 6, heat dissipation section of thick bamboo subassembly 7, frame roof beam locating component 8 on the skeleton subassembly 1, nose cone locating component 2 arranges skeleton subassembly 1's foremost in, nose cone locating component 2 rear is arranged in to preceding landing frame group price 3, jig plate subassembly 5 distributes in skeleton subassembly 1 middle part, wing subassembly 6 distributes in skeleton subassembly 1 both sides, heat dissipation section of thick bamboo subassembly 7, frame roof beam locating component 8 arranges the rear portion of skeleton subassembly 1 in, cardboard locating component 4 all arranges on skeleton subassembly 1 upper portion with frame roof beam locating component 8.

Example 2:

the present embodiment further defines the structure of the framework assembly 1 on the basis of the above embodiments, as shown in fig. 2, the framework assembly 1 is mainly composed of a framework main body 11, a corner support 12 and an anchor bolt 13; the framework main body 11 is a giant frame consisting of a plurality of square steels and steel plates and used for supporting and installing the tool positioner, the square steels are connected through the square steel plates 12, the square steels are convenient to detach and meet the requirement of green manufacturing, and the lower portion of the framework main body 11 is provided with a plurality of foundation bolts 13 which can be used for leveling the tool framework to achieve the supporting effect. Other parts of this embodiment are the same as those of the above embodiment, and are not described again.

Example 3:

in this embodiment, based on the above embodiments, the structure of the nose cone positioning assembly 2 is further defined, as shown in fig. 3 and 4, the nose cone positioning assembly 2 is mainly composed of a vertical column 21, a double-guide-rod positioner 22, a nose cone clamping plate 23, a frame positioning plate 24, a bolt 25, an end surface clamping plate 26, a web stringer positioner 27 and a connecting support 28; the nose cone clamping plate 23 is formed by welding four clamping plates into a cross shape, and the shape of each clamping plate is consistent with that of the nose cone of the airplane; the double-guide-rod positioner 22 moves linearly along the direction of the guide rod to push the nose cone clamping plate 23 to tightly press the nose cone of the airplane for positioning; the frame positioning plate 24 and the end face clamping plate 26 position and hold the airplane frame through the positioning pin 25 and the web stringer positioner 27. Other parts of this embodiment are the same as those of the above embodiment, and are not described again.

Example 4:

in this embodiment, on the basis of the above embodiment, the structure of the front landing gear set 3 is further defined, as shown in fig. 5, the front landing gear set 3 is mainly composed of a cross beam 31, a stopper 32 and a plug 33; crossbeam 31 is fixed in skeleton subassembly 1 top, dog 32 is fixed to be set up in crossbeam 31 middle part, is provided with a plurality of bolts 33 on the dog 32. Other parts of this embodiment are the same as those of the above embodiment, and are not described again.

Example 5:

in this embodiment, on the basis of the above embodiments, the structure of the card board positioning assembly 4 is further limited, as shown in fig. 6, the card board positioning assembly 4 mainly comprises a front body card board 41, a middle body card board 42, a rear body card board 43 and a rear body back card board 44, the front body card board 41, the middle body card board 42, the rear body card board 43 and the rear body back card board 44 can position and assemble the frame beam of the airplane body, and each card board is fed through a spiral positioner to compress and hold the frame of the airplane body. Other parts of this embodiment are the same as those of the above embodiment, and are not described again.

Example 6:

in this embodiment, the structure of the drill plate assembly 5 is further defined on the basis of the above embodiment, as shown in fig. 7, the drill plate assembly 5 mainly comprises a plurality of supports 51 and a plurality of drill plates 52, the drill plates 52 are mounted on the supports 51, bushings for drilling positioning holes in the fuselage are mounted in the drill plates 52, and each support 51 is fixedly connected with the framework assembly 1 through bolts. Other parts of this embodiment are the same as those of the above embodiment, and are not described again.

Example 7:

in this embodiment, based on the above embodiment, the structure of the wing assembly 6 is further defined, as shown in fig. 8, the wing assembly 6 is mainly composed of a clasper 61 and an adjustable strut 62, the clasper 61 can position and hold the wing of the aircraft, and the adjustable strut 62 can adjust the posture of the wing of the aircraft to participate in the involution assembly of the wing and the fuselage. Other parts of this embodiment are the same as those of the above embodiment, and are not described again. Other parts of this embodiment are the same as those of the above embodiment, and are not described again.

Example 8:

the present embodiment further defines the structure of the clasper 61 on the basis of the above embodiments, as shown in fig. 9, the clasper 61 is mainly composed of a screw 611, a tangential compressor 612, an upper pressure plate 613, a spring 614, a T-shaped key 615, a lower pressure plate 616, a hand wheel 617, a nut 618, a screw positioner 619 and a welding support 620; the upper pressing plate 613 is pressed by the tangential pressing 612 and fixed on the screw 611; the lower pressing plate 616 is positioned on the screw 611 through the T-shaped key 615, the hand wheel 617 is rotated to drive the lower pressing plate 616 to move axially, and after the lower pressing plate is in place, the nut 618 is screwed down to perform self-locking; the spring 614 is used for axially pressing and positioning the upper pressure plate 613 and the lower pressure plate 616; the overall mechanism of the spiral positioner 619 performs axial movement and positioning. Other parts of this embodiment are the same as those of the above embodiment, and are not described again.

Example 9:

the present embodiment further defines the structure of the adjustable strut 62 on the basis of the above embodiments, as shown in fig. 10, the adjustable strut 62 is mainly composed of a supporting roller 621, a positioner 622, and a welding support 623; a layer of felt is adhered to the surface of the supporting wheel 621, the felt is in direct contact with an airplane body and can be adjusted up and down under the action of the positioner 622, and the airplane body can move back and forth by rolling on the supporting wheel 621, so that the posture of a product is adjusted. Other parts of this embodiment are the same as those of the above embodiment, and are not described again.

It is understood that the working principle and working process of the integrated whole machine assembly tool structure according to one embodiment of the present invention, such as the heat dissipation cylinder assembly 7 and the frame beam positioning assembly 8, are well known in the art and will not be described in detail herein.

While embodiments of the invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.

Claims

1. An integrated full-machine assembly tool is characterized by comprising a framework component (1), the framework component (1) is provided with a nose cone positioning component (2), a front landing frame component (3), a clamping plate positioning component (4), a drilling template component (5), a wing component (6), a heat radiation barrel component (7) and a frame beam positioning component (8), the nose cone positioning component (2) is arranged at the foremost end of the framework component (1), the front landing frame set price (3) is arranged behind the nose cone positioning component (2), the drill plate components (5) are distributed in the middle of the framework component (1), the wing components (6) are distributed on two sides of the framework component (1), the heat radiation barrel assembly (7), the frame beam positioning assembly (8) is arranged at the rear part of the framework assembly (1), the clamping plate positioning assembly (4) and the frame beam positioning assembly (8) are arranged at the upper part of the framework assembly (1); the framework component (1) mainly comprises a framework main body (11), a corner support (12) and foundation bolts (13); the nose cone positioning assembly (2) mainly comprises a stand column (21), a double-guide-rod positioner (22), a nose cone clamping plate (23), a frame positioning plate (24), a positioning pin (25), an end-face clamping plate (26), a web stringer positioner (27) and a connecting support (28); the front landing frame assembly (3) mainly comprises a cross beam (31), a stop block (32) and a bolt (33); the clamping plate positioning assembly (4) mainly comprises a front machine body clamping plate (41), a middle machine body clamping plate (42), a rear machine body clamping plate (43) and a rear machine body back clamping plate (44); the drilling template component (5) mainly comprises a plurality of supports (51) and a plurality of drilling templates (52).

2. The integrated full-machine assembly tool according to claim 1, wherein the framework main body (11) is a giant frame composed of a plurality of square steels and steel plates, the square steels are connected through angle braces (12), and a plurality of anchor bolts (13) are arranged at the lower part of the framework main body (11).

3. The integrated full-machine assembly tool according to claim 1 or 2, wherein the nose cone clamping plates (23) are welded into a cross shape by four clamping plates, and the shape of each clamping plate is consistent with that of the nose cone of the airplane; the double-guide-rod positioner (22) moves linearly along the direction of the guide rod to push the nose cone clamping plate (23) to tightly press the nose cone of the airplane for positioning; the frame positioning plate (24) and the end face clamping plate (26) position and fix the airplane frame through the positioning pin (25) and the web stringer positioner (27).

4. The integrated full-machine assembly tool according to claim 1 or 2, wherein the cross beam (31) is fixed above the framework component (1), the stop block (32) is fixedly arranged in the middle of the cross beam (31), and a plurality of bolts (33) are arranged on the stop block (32).

5. The integrated full-machine assembly tool according to claim 1 or 2, wherein the front machine body clamping plate (41), the middle machine body clamping plate (42), the rear machine body clamping plate (43) and the rear machine body back clamping plate (44) can position and assemble the frame beam of the airplane body, and the clamping plates are fed through the spiral positioner to compress and fix the added frame of the airplane.

6. The integrated full-machine assembly tool according to claim 1 or 2, wherein the drill plate (52) is mounted on a support (51), a bushing for drilling a positioning hole in a machine body is mounted in the drill plate (52), and each support (51) is fixedly connected with the framework component (1) through a bolt.

7. The integrated full-aircraft assembly tool according to claim 1 or 2, wherein the wing assembly (6) mainly comprises a locking device (61) and an adjustable strut (62), the locking device (61) can position and hold the aircraft wing, and the adjustable strut (62) can adjust the aircraft wing to participate in the involutory assembly of the wing and the fuselage.

8. The integrated full-machine assembly tool according to claim 7, wherein the tightener (61) mainly comprises a screw (611), a tangential compactor (612), an upper pressure plate (613), a spring (614), a T-shaped key (615), a lower pressure plate (616), a hand wheel (617), a nut (618), a spiral positioner (619) and a welding support (620); the upper pressure plate (613) is pressed by a tangential presser (612) and fixed on the screw (611); the lower pressing plate (616) is positioned on the screw rod (611) through the T-shaped key (615), the hand wheel (617) is rotated to drive the lower pressing plate (616) to axially move, and after the lower pressing plate (616) is in place, the nut (618) is screwed to perform self-locking; the spring (614) is used for axially pressing and positioning the upper pressure plate (613) and the lower pressure plate (616); the integral mechanism of the spiral positioner (619) performs axial movement and positioning.

9. The integrated full-machine assembly tool according to claim 7, wherein the adjustable support rod (62) mainly comprises a supporting wheel (621), a positioner (622) and a welding support (623); a layer of felt is adhered to the surface of the supporting wheel (621) and is in direct contact with the airplane body, the upper and lower adjustment can be carried out under the action of the positioner (622), and the airplane body can move back and forth by rolling on the supporting wheel (621), so that the posture of the product can be adjusted.