CN115042456B - Stringer positioning tool for manufacturing composite material fuselage wall plate and application method thereof - Google Patents
Stringer positioning tool for manufacturing composite material fuselage wall plate and application method thereof Download PDFInfo
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- CN115042456B CN115042456B CN202210649723.9A CN202210649723A CN115042456B CN 115042456 B CN115042456 B CN 115042456B CN 202210649723 A CN202210649723 A CN 202210649723A CN 115042456 B CN115042456 B CN 115042456B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
- B29C70/541—Positioning reinforcements in a mould, e.g. using clamping means for the reinforcement
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
- B29C70/543—Fixing the position or configuration of fibrous reinforcements before or during moulding
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3082—Fuselages
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention relates to a stringer positioning tool for manufacturing a composite material fuselage wallboard, which comprises a plurality of groups of stringer positioning clamping plates, wherein the stringer positioning clamping plates are used for forming assembly with the wallboard and positioning stringers in the reinforced wallboard; the stringer positioning clamping plate comprises a tool skeleton main body, a connecting positioning assembly and a positioning pressing assembly, wherein two ends of the tool skeleton main body are fixedly connected with the wallboard forming tool through the connecting positioning assembly; the plurality of positioning and compacting assemblies are sequentially arranged at intervals along the span direction of the tool skeleton main body and are used for positioning stringers of corresponding section positions. The invention also relates to a using method of the stringer positioning tool for manufacturing the composite material fuselage wall plate. The stringer positioning tool for manufacturing the composite material fuselage wallboard and the using method aim at solving the problems of poor wallboard gluing quality, large stringer axis position deviation and complicated positioning mode operation caused by stringer position sliding in the curing process of the large-size complex curvature composite material fuselage wallboard.
Description
Technical Field
The invention relates to the technical field of composite material manufacturing, in particular to a stringer positioning tool for manufacturing a composite material fuselage wallboard and a using method thereof.
Background
The biggest structural unit in the aircraft fuselage structure is the wallboard (skin and stringer), also is the most serious structural component of atress, and the majority load of fuselage all needs to be transmitted through the wallboard, and the stringer is as the longitudinal member of fuselage structure, mainly is used for bearing the axial force that the fuselage crooked causes in the stringer type fuselage, and the stringer has the supporting role to the skin in addition, and it has improved the compressive of skin, has cut unstability critical stress, and the accuracy of stringer relative position very big influences the overall structure performance of fuselage wallboard.
The common stringer structures in the composite material fuselage panel parts are T-shaped, omega-shaped and the like, and as the fuselage structure needs the change of the double-curvature, large-thickness and large-opening structure of the skin inner profile, the stringer can change along with the change of the skin inner profile structure. The conventional manufacturing scheme of the composite material fuselage panel is that a cured 'dry' stringer and a wet skin which is not cured and paved by a female die are glued and formed, and as the cured 'dry' stringer is of an elongated structure, the cross section of the stringer is smaller, the length is longer, the stiffness of the stringer is insufficient, and particularly for the stringer with a higher radian, the stringer is deformed due to dead weight in a natural state; because the skin has certain thickness deviation before and after solidification and complex thickness change areas exist in the skin structure, the problem that the stringer bonding interface is not matched with the skin interface often occurs, and the position accuracy and bonding quality of the stringer axis cannot be ensured in the co-bonding process; in the co-cementing and curing process, the phenomenon that the stringer slides to the position of the radian bottom can occur, so that auxiliary materials are mixed on a cementing interface, and manufacturing defects occur; in the use process of the traditional stringer positioning tool, the positioning tool cannot move, the positioning molded surface needs to be considered to prevent interference, the positioning precision is reduced, the positioning molded surface is too close to the molded surface of the part, and the part is extremely easy to collide when the positioning tool is disassembled and assembled, so that the part is damaged; and in part of traditional location frock needs to reserve positioner to vacuum bag film, complex operation, and the condition that appears vacuum easily reveal all seriously influences fuselage wallboard overall quality.
Therefore, the inventor provides a stringer positioning tool for manufacturing a composite material fuselage panel and a using method thereof.
Disclosure of Invention
(1) Technical problem to be solved
The embodiment of the invention provides a stringer positioning tool for manufacturing a composite material fuselage wallboard and a using method thereof, which solve the technical problems of poor wallboard gluing quality, large stringer axis position deviation and complicated positioning mode operation caused by stringer position sliding in the curing process of the large-size complex curvature composite material fuselage wallboard.
(2) Technical proposal
The invention provides a stringer positioning tool for manufacturing a composite material fuselage wallboard, which comprises a plurality of groups of stringer positioning clamping plates, wherein the stringer positioning clamping plates are used for forming and assembling with the wallboard and positioning stringers in the reinforced wallboard; wherein, the liquid crystal display device comprises a liquid crystal display device,
the stringer positioning clamping plate comprises a tool skeleton main body, a connecting positioning assembly and a positioning and compacting assembly, wherein two ends of the tool skeleton main body are fixedly connected with the wallboard forming tool through the connecting positioning assembly; the positioning and compacting assemblies are sequentially arranged at intervals along the span direction of the tool skeleton main body and used for positioning stringers at corresponding section positions.
Further, limit round holes for positioning the connecting and positioning assembly are formed in the base on two sides of the tool skeleton main body.
Further, connect locating component including guide pin axle, reinforcing backing plate, fixation nut and first fixing bolt, guide pin axle, reinforcing backing plate, fixation nut install in the both sides platform of wallboard shaping frock, fixation nut is used for fixing guide pin axle, reinforcing backing plate locates guide pin axle with between the fixation nut and be fixed in the side platform butt joint face back of wallboard shaping frock, first fixing bolt is located guide pin axle's both sides just are used for fixed connection frock skeleton main part wallboard shaping frock.
Further, the positioning and compacting assembly comprises a fixed part and a moving part; one end of the fixing part is arranged at the lower end of the tool skeleton main body, and the moving part is arranged at the other end of the fixing part and used for elastically positioning the stringers.
Further, the fixing part comprises a fixing pin and a connecting piece, and the moving part comprises a moving handle, a guide post, a compression nut, a molded surface positioning block and an elastic element;
the connecting piece is sleeved at the first end of the guide post and is used for connecting the tool skeleton main body, the profile positioning block is movably connected to the second end of the guide post, a plurality of fixing pin holes matched with the fixing pins are formed in the guide post along the axial direction of the guide post, and the moving handle is fixedly connected with the guide post and is used for driving the guide post to move along the axial direction of the connecting piece;
the compression nut is in threaded connection with the guide post, and the elastic element is sleeved on the guide post and is positioned between the compression nut and the molded surface positioning block.
Further, the moving part further comprises a limiting pin, and the profile positioning block is movably connected to the guide post through the limiting pin;
the limiting pin is sequentially inserted into the guide post, the molded surface positioning block and can move along the axial direction of the guide post.
Further, the limiting pin holes formed in the profile positioning blocks are kidney-shaped holes.
Further, the inner profile of the profile locating block is adapted to the theoretical outer profile of the stringer.
Further, a reserved gap is reserved between the inner surface of the profile positioning block and the theoretical outer profile of the stringer.
The invention also provides a use method of the stringer positioning tool for manufacturing the composite material fuselage wall plate, which comprises the following steps:
1) Installing a plurality of groups of stringer positioning clamping plates on the positioning section of the wallboard forming tool, so that the positioning pressing assembly of each stringer positioning clamping plate is positioned and fixed at an initial position far away from the stringer;
2) Pressing the cementing surfaces of the stringers after installing each stringer on the stiffened panel, and placing an auxiliary assembly on each stringer;
3) Controlling the positioning and compacting assembly of each stringer positioning clamping plate to move to a final use position so as to be attached to the auxiliary assembly and fixed;
4) Positioning each stringer is completed in sequence, end packaging is carried out, and a curing process is carried out;
5) After curing, all positioning and compacting assemblies are controlled to move to an initial position far away from the stringers and fixed, and the stringer positioning clamping plates are adjusted away.
(3) Advantageous effects
In summary, the positioning clamping plate is arranged on the positioning interface, the positioning relation is established between the bases on two sides of the tool framework main body and the wallboard forming tool, the positioning pressing assembly is controlled to press the stringers to be attached to the inner molded surface of the skin, a certain normal pressing force is applied, the part to be bonded is pressed by simulating manual operation, the normal pressing force can adapt to thickness change before and after skin solidification, the pressing force is continuously applied in the whole solidification forming process, the positioning pressing assembly can effectively control the position precision of the appearance surface of the stringers, the positioning can be fast and accurately performed, the operation steps are simple, the positioning reliability is high, the stringers are effectively prevented from deviating in the solidification process, the situation that the positioning tool collides with the part in the use process is avoided, and the forming quality of the wallboard part with large size and complex curvature is effectively improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are needed in the embodiments of the present invention will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort to a person of ordinary skill in the art.
FIG. 1 is an assembly schematic diagram of a stringer positioning tooling for manufacturing a composite fuselage panel according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a stringer locating clamping plate of a stringer locating tool for manufacturing a composite fuselage panel according to an embodiment of the present invention;
FIG. 3 is an enlarged view at A in FIG. 2;
FIG. 4 is a schematic structural view of a connection positioning assembly of a stringer positioning tool for manufacturing a composite fuselage panel according to an embodiment of the present invention;
FIG. 5 is a schematic structural view of a positioning and compaction assembly of a stringer positioning tool for manufacturing a composite fuselage panel according to an embodiment of the present invention;
FIG. 6 is a schematic view of a first operational state of the positioning and compression assembly according to an embodiment of the present invention;
fig. 7 is a schematic diagram of a second action state of the positioning and compressing assembly according to an embodiment of the present invention.
In the figure:
1-a wallboard forming tool; 2-a reinforced wallboard; 201-stringers; 202-covering; 3-stringer positioning clips; 301-a tool skeleton main body; 302-connecting a positioning component; 3021-guiding pin shafts; 3022-reinforcing backing plates; 3023-securing the nut; 3024-a first fixing bolt; 303-positioning a compaction assembly; 3031-fixing pins; 3032-connectors; 3033-a motion handle; 3034-guiding columns; 3035-a compression nut; 3036-profile positioning block; 3037-elastic elements; 3038-a limiting pin; 3039-fixing bolts; 304-a framework hanging ring; 4-auxiliary assembly.
Detailed Description
Embodiments of the present invention are described in further detail below with reference to the accompanying drawings and examples. The following detailed description of the embodiments and the accompanying drawings are provided to illustrate the principles of the invention and are not intended to limit the scope of the invention, i.e., the invention is not limited to the embodiments described, but covers any modifications, substitutions and improvements in parts, components and connections without departing from the spirit of the invention.
In the description of the present invention, it should be understood that the directions or positional relationships indicated by the terms "upper", "lower", "front", "rear", etc. are based on the directions or positional relationships shown in the drawings, or the directions or positional relationships conventionally put in place when the product of the present invention is used, or the directions or positional relationships conventionally understood by those skilled in the art are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or elements to be referred to must have a specific direction, be constructed and operated in a specific direction, and therefore should not be construed as limiting the present invention.
In the description of the present invention, it should also be noted that, unless explicitly stated and limited otherwise, the terms "disposed" and "mounted" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be directly connected or indirectly connected through an intermediate medium. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
It should be noted that, in the case of no conflict, the embodiments and features in the embodiments may be combined with each other. The present application will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
Fig. 1 is a schematic structural diagram of a stringer positioning tool for manufacturing a composite material fuselage panel according to an embodiment of the present invention, as shown in fig. 1-2, the positioning tool may include a plurality of stringer positioning clamping plates 3, where the stringer positioning clamping plates 3 are used to match with the panel forming tool 1 and position the stringers 201 in the reinforced panel 2; the stringer positioning clamping plate 3 comprises a tool skeleton main body 301, a connecting positioning assembly 302 and a positioning and compacting assembly 303, wherein two ends of the tool skeleton main body 301 are fixedly connected with the wallboard forming tool 1 through the connecting positioning assembly 302; the plurality of positioning and compacting assemblies 303 are sequentially arranged at intervals along the span direction of the tool skeleton main body 301 and are used for positioning the stringers 201 at corresponding section positions.
In the above embodiments, stringer 201 may be an omega-shaped stringer or a T-shaped stringer. According to the structural characteristics of the large-size complex curvature fuselage wall panel, the positioning interface can be determined by the multiple groups of stringer positioning clamping plates 3 according to the characteristics of stringers in the reinforced wall panel, and the positioning positions are set. The material of the stringer positioning clamping plate 3 can be selected from invar steel materials consistent with the wallboard forming tool 1, so that the problem of deformation coordination in a high-temperature environment is solved.
Through the base of frock skeleton main part 301 both sides and wallboard shaping frock 1 establishment positional relationship, control location compress tightly subassembly 303 makes stringer 201 compress tightly the interior profile of laminating skin 202 to exert certain normal compressive force, location compress tightly the positional accuracy of the long stringer 201 appearance face of subassembly 303 control, location that can be quick accurate, operating procedure is simple, and location reliability is strong, effectively prevents that stringer 201 from producing the skew in the solidification process.
Wherein the positioning and compression assemblies 303 individually control the position of each stringer 201 at each positioning interface, each positioning and compression assembly 303 does not interfere with each other.
Meanwhile, a framework hanging ring 304 is arranged at the upper end part of the tool framework main body 301, so that the tool framework main body 301 can be conveniently lifted.
As an alternative embodiment, as shown in fig. 2, the bases on two sides of the tool skeleton body 301 are provided with limiting round holes for positioning with the connection positioning assembly 302. The limiting round hole is mainly formed to be matched with the fixed guide pin shaft 3021, so that the tool skeleton main body 301 is fixed on the wallboard forming tool 1 to form an integral tool.
As an alternative embodiment, as shown in fig. 4, the connection positioning assembly 302 includes a guide pin 3021, a reinforcing pad 3022, a fixing nut 3023 and a first fixing bolt 3024, where the guide pin 3021, the reinforcing pad 3022, and the fixing nut 3023 are installed on two side platforms of the wall board forming tool 1, the fixing nut 3023 is used for fixing the guide pin 3021, the reinforcing pad 3022 is located between the guide pin 3021 and the fixing nut 3023 and is fixed on the back of the butt joint surface of the side platform of the wall board forming tool 1, and the first fixing bolt 3024 is located on two sides of the guide pin 3021 and is used for fixedly connecting the tool skeleton body 301 and the wall board forming tool 1.
The above embodiment gives a specific structural form of the connection positioning assembly 302, and the reinforcing pad 3022 is provided to make the installation between the guide pin 3021 and the fixing nut 3023 more stable. The first fixing bolt 3024 is used for further improving the stability of the fixture skeleton body 301 after being fixedly mounted with the wall plate forming fixture 1.
As an alternative embodiment, the positioning compression assembly 303 includes a fixed portion and a moving portion; one end of the fixing portion is mounted at the lower end of the tool skeleton main body 301, and the moving portion is disposed at the other end of the fixing portion and is used for elastically positioning the stringer 201. Wherein, the fixing part is used for fixedly connecting the positioning and compressing assembly 303 with the tool skeleton main body 301; the purpose of the kinematic section is to resiliently position stringer 201 to prevent stringer 201 from shifting during curing.
As an alternative embodiment, as shown in fig. 3 and 5, the fixing portion includes a fixing pin 3031 and a connecting piece 3032, and the moving portion includes a moving handle 3033, a guide post 3034, a compression nut 3035, a profile positioning block 3036 and an elastic element 3037; the connecting piece 3032 is sleeved at the first end of the guide post 3034 and is used for connecting the tool skeleton main body 301, the profile positioning block 3036 is movably connected to the second end of the guide post 3034, a plurality of fixing pin holes matched with the fixing pins 3031 are formed in the axial direction of the guide post 3034, and the moving handle 3033 is fixedly connected with the guide post 3034 and is used for driving the guide post 3034 to move along the axial direction of the connecting piece 3032; the compression nut 3035 is screwed to the guide post 3034, and the elastic element 3037 is sleeved on the guide post 3034 and is located between the compression nut 3035 and the profile positioning block 3036.
In the above embodiment, the connector 3032 may be specifically a hollow structure and has a mounting plate, and is fixedly connected with the tool skeleton main body 301 through the mounting plate, so that in order to facilitate the movement of the moving handle 3033 along the axial direction of the connector 3032, a notch may be formed on the outer wall of the connector 3032 along the axial direction thereof; the elastic element 3037 may be a spring, where two ends of the spring are respectively limited by the compression nut 3035 and the profile positioning block 3036, and the relative position of the compression nut 3035 on the guide post 3034 is controlled to compress or loosen the spring, so that the profile positioning block 3036 has a certain normal load, and the stringer 201 can adapt to the thickness of the skin 202 before and after curing.
Two fixation pin holes are generally formed along the axial direction of the guide post 3034 to satisfy two status positions of the profile block 3036 (one is the initial position away from the stringer 201 and the other is the use position of the attachment aid assembly 4).
As an alternative embodiment, as shown in fig. 5, the moving part further includes a limiting pin 3038, and the profile positioning block 3036 is movably connected to the guide post 3034 by the limiting pin 3038; the stopper pin 3038 is sequentially inserted into the guide post 3034 and the profile positioning block 3036 and is movable in the axial direction of the guide post 3034.
Specifically, the guide post 3034 drives the profile positioning block 3036 to move up and down along the axial direction of the connector 3032 by using the limiting pin 3038.
As an alternative embodiment, as shown in fig. 6-7, a kidney-shaped hole is formed on the profile positioning block 3036. The kidney-shaped hole can enable axial movement of the profile block 3036 relative to the guide post 3034, so that the compression degree of the profile block 3036 on the stringer 201 is properly adjusted.
As an alternative embodiment, the inner profile of profile block 3036 is adapted to the theoretical outer profile of stringer 201. The profile positioning block 3036 can be attached to the stringer 201 more, so that the stringer 201 is ensured to be more stable in the positioning process and does not deviate.
As an alternative embodiment, there is a clearance gap between the inner surface of profile block 3036 and the theoretical outer profile of stringer 201. The setting of the reserved gap is to place an auxiliary assembly 4 on the surface of the stringer 201, and the setting is performed in consideration of the thickness of auxiliary materials and the positioning accuracy requirement of the molded surface, and the interval of 0.2 mm-0.5 mm is reserved.
The auxiliary component 4 is a generic term for a vacuum auxiliary material that is essential in the composite material forming process, and mainly comprises a vacuum bag film, a barrier film, an airfelt, a strippable cloth, and the like, and has the function of completely covering and attaching to the surface of the stringer 201 to provide a vacuum environment.
The embodiment of the invention also provides a use method of the stringer positioning tool for manufacturing the composite material fuselage wall plate, which comprises the following steps:
s100, installing a plurality of groups of stringer positioning clamping plates 3 on the positioning section of the wallboard forming tool 1, and enabling the positioning and pressing assembly 303 of each stringer positioning clamping plate 3 to be in an initial position far away from the stringer 201 and fixed;
s200, after each stringer 201 is installed on the reinforced wallboard 2, pressing the cementing surface of the stringer 201, and placing an auxiliary assembly 4 on each stringer 201;
s300, controlling the positioning and pressing assembly 303 of each stringer positioning clamping plate 3 to move to a final use position so as to be attached to the auxiliary assembly 4 and fixed;
s400, positioning each stringer 201 in sequence, packaging the end part, and performing a curing process;
and S500, after curing is completed, controlling all the positioning and pressing assemblies 303 to move to an initial position far away from the stringer 201 and fixing, and adjusting the stringer positioning clamping plate 3.
In the above embodiment, in step S100, a plurality of sets of stringer positioning clips are mounted on the positioning section of the wallboard forming tool using a crane, and the moving handle is controlled to make the moving parts of the positioning and compacting assemblies of all the stringer positioning clips at the initial positions far away from the molding surface, and fixed using a fixing pin.
In step S200, the operator installs each glued stringer from the top of the arc to the bottom of the arc according to the projection score line of the laser positioner or the tip positioner, presses the glued stringer surface after each stringer is placed, and places an auxiliary material on each stringer.
In step S300, the moving handle is controlled to move the guide post to the final use position by the moving part of the positioning and pressing assembly of the multi-group stringer positioning tool corresponding to the stringer for placing auxiliary materials, and the fixing pin is used for fixing, the pressing nut is adjusted, so that the profile positioning block has a certain pressing force, and the profile of the profile positioning block is pressed close to the auxiliary materials outside the stringer.
In step S500, after curing is completed, each moving handle on each set of positioning tools is controlled to move the moving part of the positioning and compacting assembly of all the stringer positioning tools to an initial position far away from the molded surface, and the moving part is fixed by using a fixing pin, and the stringer positioning tools are adjusted by using a crane.
It should be understood that, in the present specification, each embodiment is described in an incremental manner, and the same or similar parts between the embodiments are all referred to each other, and each embodiment is mainly described in a different point from other embodiments. The invention is not limited to the specific steps and structures described above and shown in the drawings. Also, a detailed description of known method techniques is omitted here for the sake of brevity.
The foregoing is merely an example of the present application and is not limited to the present application. Various modifications and alterations of this application will become apparent to those skilled in the art without departing from the scope of this invention. Any modifications, equivalent substitutions, improvements, etc. which are within the spirit and principles of the present application are intended to be included within the scope of the claims of the present application.
Claims (8)
1. The stringer positioning tool for manufacturing the composite material fuselage wallboard is characterized by comprising a plurality of groups of stringer positioning clamping plates (3), wherein the stringer positioning clamping plates (3) are used for being matched with the wallboard forming tool (1) and positioning stringers (201) in the reinforced wallboard (2); wherein, the liquid crystal display device comprises a liquid crystal display device,
the stringer positioning clamping plate (3) comprises a tool skeleton main body (301), a connecting and positioning assembly (302) and a positioning and pressing assembly (303), wherein two ends of the tool skeleton main body (301) are fixedly connected with the wallboard forming tool (1) through the connecting and positioning assembly (302); the positioning and compacting assemblies (303) are sequentially arranged at intervals along the span direction of the tool skeleton main body (301) and are used for positioning stringers (201) of corresponding section positions;
the positioning and compacting assembly (303) comprises a fixed part and a moving part; one end of the fixing part is arranged at the lower end of the tool skeleton main body (301), and the moving part is arranged at the other end of the fixing part and is used for elastically positioning the stringer (201);
the fixing part comprises a fixing pin (3031) and a connecting piece (3032), and the moving part comprises a moving handle (3033), a guide post (3034), a compression nut (3035), a profile positioning block (3036) and an elastic element (3037);
the connecting piece (3032) is sleeved at the first end of the guide post (3034) and is used for connecting the tool skeleton main body (301), the profile positioning block (3036) is movably connected to the second end of the guide post (3034), a plurality of fixing pin holes matched with the fixing pins (3031) are formed in the guide post (3034) along the axial direction of the guide post, and the moving handle (3033) is fixedly connected with the guide post (3034) and is used for driving the guide post (3034) to move along the axial direction of the connecting piece (3032);
the compression nut (3035) is in threaded connection with the guide post (3034), and the elastic element (3037) is sleeved on the guide post (3034) and is located between the compression nut (3035) and the profile positioning block (3036).
2. The stringer positioning tool for manufacturing a composite material fuselage panel according to claim 1, wherein limiting round holes for positioning with the connecting and positioning assembly (302) are formed on bases on two sides of the tool skeleton main body (301).
3. The stringer positioning tool for manufacturing a composite material fuselage panel according to claim 1, wherein the connection positioning assembly (302) comprises a guide pin shaft (3021), a reinforcing base plate (3022), a fixing nut (3023) and a first fixing bolt (3024), the guide pin shaft (3021), the reinforcing base plate (3022) and the fixing nut (3023) are mounted on two side platforms of the panel forming tool (1), the fixing nut (3023) is used for fixing the guide pin shaft (3021), the reinforcing base plate (3022) is arranged between the guide pin shaft (3021) and the fixing nut (3023) and is fixed on the back of a butt joint surface of a side platform of the panel forming tool (1), and the first fixing bolt (3024) is located on two sides of the guide pin shaft (3021) and is used for fixedly connecting the tool skeleton main body (301) and the panel forming tool (1).
4. The stringer positioning tool for manufacturing a composite material fuselage panel according to claim 1, wherein the moving portion further includes a stopper pin (3038), and the profile positioning block (3036) is movably connected to the guide post (3034) by the stopper pin (3038);
the limiting pin (3038) is sequentially inserted into the guide post (3034) and the profile positioning block (3036) and can move along the axial direction of the guide post (3034).
5. The stringer positioning tooling for manufacturing a composite material fuselage panel of claim 4, wherein the limit pin holes formed in the profile positioning block (3036) are kidney-shaped holes.
6. Stringer positioning fixture for the manufacture of fuselage panels of composite material according to claim 1, characterized in that the inner surface of the profile positioning block (3036) is adapted to the theoretical outer profile of the stringer (201).
7. The stringer positioning tooling for the manufacture of composite fuselage panels of claim 6, wherein a clearance is provided between the inner surface of the profile block (3036) and the theoretical outer profile of the stringer (201).
8. A method of using the stringer positioning tooling for the manufacture of composite fuselage panels as defined in any one of claims 1 to 7, the method comprising the steps of:
1) Installing a plurality of groups of stringer positioning clamping plates (3) on the positioning section of the wallboard forming tool (1), and enabling the positioning pressing assembly (303) of each stringer positioning clamping plate (3) to be positioned and fixed at an initial position far away from the stringer (201);
2) Pressing the cementing surface of the stringers (201) after installing each stringer (201) on the stiffened panel (2), placing an auxiliary assembly (4) on each stringer (201);
3) Controlling the positioning and pressing assembly (303) of each stringer positioning clamping plate (3) to move to a final use position so as to be attached to the auxiliary assembly (4) and fixed;
4) Positioning each stringer (201) in turn, and performing end encapsulation, curing;
5) After curing, all positioning and pressing assemblies (303) are controlled to move to an initial position far away from the stringer (201) and fixed, and the stringer positioning clamping plate (3) is adjusted.
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| CN202210649723.9A CN115042456B (en) | 2022-06-10 | 2022-06-10 | Stringer positioning tool for manufacturing composite material fuselage wall plate and application method thereof |
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| CN115609057B (en) * | 2022-11-22 | 2023-04-28 | 成都市鸿侠科技有限责任公司 | Positioning tool for large arc-shaped skin |
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