CN115042456A - Stringer positioning tool for manufacturing composite material fuselage wallboard and using method thereof - Google Patents
Stringer positioning tool for manufacturing composite material fuselage wallboard and using method thereof Download PDFInfo
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- CN115042456A CN115042456A CN202210649723.9A CN202210649723A CN115042456A CN 115042456 A CN115042456 A CN 115042456A CN 202210649723 A CN202210649723 A CN 202210649723A CN 115042456 A CN115042456 A CN 115042456A
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- 239000002131 composite material Substances 0.000 title claims abstract description 32
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 29
- 238000000034 method Methods 0.000 title claims abstract description 23
- 238000003825 pressing Methods 0.000 claims abstract description 23
- 230000006835 compression Effects 0.000 claims description 23
- 238000007906 compression Methods 0.000 claims description 23
- 230000003014 reinforcing effect Effects 0.000 claims description 10
- 230000000712 assembly Effects 0.000 claims description 7
- 238000000429 assembly Methods 0.000 claims description 7
- 238000004806 packaging method and process Methods 0.000 claims description 3
- 238000007711 solidification Methods 0.000 claims description 3
- 230000008023 solidification Effects 0.000 claims description 3
- 239000000853 adhesive Substances 0.000 claims description 2
- 230000001070 adhesive effect Effects 0.000 claims description 2
- 210000001503 joint Anatomy 0.000 claims description 2
- 230000008569 process Effects 0.000 abstract description 11
- 238000004026 adhesive bonding Methods 0.000 abstract description 3
- 239000000463 material Substances 0.000 description 8
- 230000008859 change Effects 0.000 description 4
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- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
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- 230000006872 improvement Effects 0.000 description 2
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- 208000004350 Strabismus Diseases 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
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- 230000008093 supporting effect Effects 0.000 description 1
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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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Textile Engineering (AREA)
- Automatic Assembly (AREA)
- Load-Bearing And Curtain Walls (AREA)
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 being assembled with a wallboard forming tool and positioning a stringer in a reinforced wallboard; the stringer positioning clamping plate comprises a tool framework main body, a connecting and positioning assembly and a positioning and pressing assembly, and two ends of the tool framework main body are fixedly connected with the wallboard forming tool through the connecting and positioning assembly; a plurality of location compress tightly the subassembly and set up and be used for the stringer of the corresponding cross-section position of location in proper order interval along the span direction of frock skeleton main part. The invention further relates to a use method of the stringer positioning tool for manufacturing the composite material fuselage wallboard. The stringer positioning tool for manufacturing the composite material fuselage wallboard and the using method aim to solve the problems of poor wallboard gluing quality, large stringer axis position deviation and complex positioning mode operation caused by stringer position slippage 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 largest structural unit in the aircraft fuselage structure is a wallboard (skin and a stringer) and is also a structural part with the most serious stress, most of loads of the fuselage are transmitted through the wallboard, the stringer is used as a longitudinal component of the fuselage structure and is mainly used for bearing axial force caused by bending of the fuselage in a stringer type fuselage, and in addition, the stringer has a supporting effect on the skin, so that the compression critical stress and shear instability critical stress of the skin are improved, and the accuracy of the relative position of the stringer greatly influences the overall structural performance of the fuselage wallboard.
Common stringer structures in composite fuselage panel parts are T-shaped, omega-shaped and the like, and due to the fact that the inner profile of a skin required by the fuselage structure is changed by a double curvature, large thickness and large opening structure, stringers can change along with the change of the inner profile structure of the skin. The common manufacturing scheme of the composite material fuselage wallboard is that a cured dry stringer and an uncured wet skin which is paved by adopting a female die are subjected to bonding molding, and the cured dry stringer is of a long and thin structure, so that the section of the stringer is smaller, the length of the stringer is longer, the rigidity of the stringer is insufficient, and particularly for the stringer at a position with higher radian, the deformation caused by self weight is often generated under a natural state; because the skin has certain thickness deviation before and after curing and a complex thickness change area exists in the skin structure, the problem that the stringer bonding interface is not matched with the skin interface often occurs, and the position precision and the bonding quality of the stringer axis cannot be ensured in the co-bonding process; in the co-bonding curing process, the phenomenon that the stringer slides to the position of the radian bottom can occur, so that the auxiliary material is mixed on the bonding interface, and the manufacturing defect occurs; in the use process of the traditional stringer positioning tool, the positioning tool cannot move, the positioning profile needs to be considered to prevent interference, the positioning precision is reduced, the positioning profile is too close to the part profile, and the parts are easy to collide when the positioning tools are disassembled and assembled, so that the parts are damaged; and some traditional positioning tools need to reserve a positioning device in the vacuum bag film, so that the operation is complicated, the condition of vacuum leakage is easy to occur, and the integral quality of the fuselage wall plate is seriously influenced.
Therefore, the inventor provides a stringer positioning tool for manufacturing a composite 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 use method thereof, and solves the technical problems of poor wallboard gluing quality, large stringer axis position deviation and complex positioning mode operation caused by stringer position slippage in the curing process of a large-size complex-curvature composite material fuselage wallboard.
(2) Technical scheme
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 being assembled with a wallboard forming tool and positioning a stringer in a reinforced wallboard; wherein,
the stringer positioning clamping plate comprises a tool framework main body, a connecting positioning assembly and a positioning pressing assembly, and two ends of the tool framework main body are fixedly connected with the wallboard forming tool through the connecting positioning assembly; a plurality of the location compresses tightly the subassembly and follows the longeron of corresponding cross-section position is set up and is used for fixing a position at the span direction interval in proper order of frock skeleton main part.
Further, two side bases of the tool framework main body are provided with limiting round holes used for being positioned by the connecting and positioning assembly.
Further, the connecting and positioning assembly comprises a guide pin shaft, a reinforcing base plate, a fixing nut and a first fixing bolt, the guide pin shaft, the reinforcing base plate and the fixing nut are mounted on platforms on two sides of the wallboard forming tool, the fixing nut is used for fixing the guide pin shaft, the reinforcing base plate is arranged between the guide pin shaft and the fixing nut and fixed on the back of the butt joint face of the side platform of the wallboard forming tool, and the first fixing bolt is located on two sides of the guide pin shaft and used for fixedly connecting the tool framework main body and the wallboard forming tool.
Further, the positioning and pressing assembly comprises a fixed part and a moving part; the one end of fixed part install in the lower extreme of frock skeleton main part, the motion portion is located the other end of fixed part just is used for carrying out elastic positioning to the stringer.
Furthermore, the fixed part comprises a fixed pin and a connecting piece, and the moving part comprises a moving handle, a guide post, a compression nut, a profile positioning block and an elastic element;
the connecting piece is sleeved at the first end of the guide column and used for connecting the tool framework main body, the profile positioning block is movably connected to the second end of the guide column, the guide column is provided with a plurality of fixing pin holes matched with the fixing pins along the axial direction of the guide column, and the moving handle is fixedly connected with the guide column and used for driving the guide column 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 located between the compression nut and the profile positioning block.
Furthermore, the motion part also 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 and the molded surface positioning block and can move along the axial direction of the guide post.
Furthermore, the limiting pin hole formed in the profile positioning block is a waist-shaped hole.
Further, the inner profile of the profile positioning block is matched with the theoretical outer profile of the stringer.
Furthermore, a reserved gap is reserved between the inner profile 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 wallboard, which comprises the following steps:
1) mounting a plurality of groups of stringer positioning clamping plates on a positioning section of a wallboard forming tool, and enabling a positioning and pressing assembly of each stringer positioning clamping plate to be positioned at an initial position far away from a stringer and fixed;
2) after each stringer is installed on the reinforced wallboard, the adhesive joint surface of the stringer is pressed, and an auxiliary assembly is placed on each stringer;
3) controlling the positioning and pressing assembly of each stringer positioning clamping plate to move to a final use position so that the positioning and pressing assembly is attached to the auxiliary assembly and fixed;
4) sequentially positioning each stringer, packaging the end parts, and curing;
5) and after the solidification is finished, controlling all the positioning and compressing assemblies to move to the initial positions far away from the stringer and fix the positioning and compressing assemblies, and adjusting away the stringer positioning clamping plates.
(3) Advantageous effects
In conclusion, the positioning clamping plate is arranged on the positioning interface, the positioning relation is established between the base on two sides of the tool framework main body and the wallboard forming tool, the positioning compression assembly is controlled to enable the stringer to be compressed and attached to the inner profile of the skin, a certain normal compression force is applied, manual operation is simulated to press the part to be bonded, the normal compression force can adapt to thickness change before and after the skin is cured, the compression force is continuously applied in the whole curing and forming process, the positioning compression assembly can effectively control the position precision of the outer profile of the stringer, rapid and accurate positioning can be achieved, the operation steps are simple, the positioning reliability is high, the stringer is effectively prevented from deviating in the curing process, the situation that the part is collided in the using process of the positioning tool is avoided, and the forming quality of large-size and complex-curvature wallboard parts is effectively improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used 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 it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is an assembly schematic view of a stringer positioning fixture for manufacturing a composite fuselage panel according to an embodiment of the present invention;
FIG. 2 is a schematic structural view of a stringer positioning clip of a stringer positioning 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 connecting and 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 diagram of a positioning and pressing 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 diagram of a first operating state of the positioning and compressing assembly provided by the embodiment of the invention;
fig. 7 is a schematic diagram of a second action state of the positioning and pressing assembly according to the embodiment of the present invention.
In the figure:
1-a wallboard forming tool; 2-ribbed wall plates; 201-stringer; 202-a skin; 3-stringer positioning snap-gauge; 301-a tool framework main body; 302-connecting a positioning assembly; 3021-guide pin; 3022-reinforcing a backing plate; 3023-fixing the nut; 3024-fixing bolts; 303-positioning the hold-down assembly; 3031-a fixed pin; 3032-a connector; 3033-sports handle; 3034-guide post; 3035-pressing the nut; 3036-positioning block of molded surface; 3037-a resilient member; 3038-a spacing pin; 3039-fixing the bolt; 304-a skeleton hoisting ring; 4-auxiliary components.
Detailed Description
The embodiments of the present invention will be described in further detail with reference to the 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, alterations, and improvements in the parts, components, and connections without departing from the spirit of the invention.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "back", and the like refer to positions or positional relationships based on those shown in the drawings, or those positions or positional relationships that are conventionally used to place the products of the present invention, or those positions or positional relationships that are conventionally understood by those skilled in the art, and are used for convenience of description and simplification of the description, but do not refer to or imply that the devices or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore, should not be considered as limiting the present invention.
In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed" and "mounted" are to be construed broadly, e.g., as being fixedly attached, detachably attached, or integrally attached; may be directly connected or indirectly connected through an intermediate. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
It should be noted that, in the present application, the embodiments and features of the embodiments may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
Fig. 1 is a schematic structural diagram of a stringer positioning tool for manufacturing a composite fuselage panel according to an embodiment of the present invention, and as shown in fig. 1-2, the positioning tool may include a plurality of sets of stringer positioning snap-gauge boards 3, where the stringer positioning snap-gauge boards 3 are used for cooperating with a panel forming tool 1 and positioning stringers 201 in a stiffened panel 2; the stringer positioning clamping plate 3 comprises a tool framework main body 301, a connecting positioning assembly 302 and a positioning pressing assembly 303, wherein two ends of the tool framework main body 301 are fixedly connected with the wallboard forming tool 1 through the connecting positioning assembly 302; the plurality of positioning compression assemblies 303 are sequentially arranged at intervals along the span direction of the tool framework main body 301 and are used for positioning the stringers 201 at the corresponding section positions.
In the above embodiments, stringer 201 may be an omega stringer or a T stringer. According to the structural characteristics of the large-size complex-curvature fuselage wallboard, the multiple groups of stringer positioning clamping plates 3 can determine a positioning interface according to the characteristics of stringers in the stiffened wallboard, and set a positioning position. The material of stringer location cardboard 3 can select for use the invar steel material unanimous with wallboard shaping frock 1, guarantees the deformation coordination problem under the high temperature environment.
The positioning relation is established between the bases on the two sides of the tool framework main body 301 and the wallboard forming tool 1, the positioning compression assembly 303 is controlled to enable the stringer 201 to compress the inner profile of the attached skin 202, a certain normal pressing force is applied, the positioning compression assembly 303 controls the position precision of the outer profile of the stringer 201, the positioning can be performed quickly and accurately, the operation steps are simple, the positioning reliability is high, and the stringer 201 is effectively prevented from deviating in the curing process.
Wherein the positioning hold-down assemblies 303 individually control the position of each stringer 201 at each positioning interface, and each positioning hold-down assembly 303 does not interfere with each other.
Meanwhile, the upper end of the tool framework main body 301 is provided with a framework lifting ring 304 so as to conveniently lift the tool framework main body 301.
As an optional implementation manner, as shown in fig. 2, two side bases of the tool skeleton main body 301 are provided with a limiting circular hole for positioning with the connecting positioning assembly 302. The limiting round hole is mainly formed to be matched with the fixed guide pin shaft 3021, so that the tool framework 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 connecting and positioning assembly 302 includes a guide pin 3021, a reinforcing pad 3022, a fixing nut 3023, and a first fixing bolt 3024, the guide pin 3021, the reinforcing pad 3022, and the fixing nut 3023 are installed on the two side platforms of the panel forming tool 1, the fixing nut 3023 is used for fixing the guide pin 3021, the reinforcing pad 3022 is disposed between the guide pin 3021 and the fixing nut 3023 and is fixed on the back of the side platform butt-joint surface of the panel forming tool 1, and the first fixing bolt 3024 is located on the two sides of the guide pin 3021 and is used for fixedly connecting the tool framework main body 301 and the panel forming tool 1.
The above embodiment shows a specific structure form of the connecting and positioning assembly 302, and the reinforcing shim plate 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 framework main body 301 after being fixedly mounted on the panel forming fixture 1.
As an alternative embodiment, the positioning and compressing assembly 303 includes a fixed part and a moving part; one end of the fixed portion is mounted at the lower end of the tool framework main body 301, and the moving portion is arranged at the other end of the fixed portion and used for elastically positioning the stringer 201. The fixing part is used for fixedly connecting the positioning compression assembly 303 with the tool framework main body 301; the function of the moving portion 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 fixed portion includes a fixed pin 3031 and a connecting member 3032, and the moving portion includes a moving handle 3033, a guiding post 3034, a pressing 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 used for connecting the tool framework main body 301, the molded surface positioning block 3036 is movably connected at the second end of the guide post 3034, the guide post 3034 is provided with a plurality of fixing pin holes matched with the fixing pin 3031 along the axial direction, and the moving handle 3033 is fixedly connected with the guide post 3034 and used for driving the guide post 3034 to move along the axial direction of the connecting piece 3032; the compression nut 3035 is screwed on the guide post 3034, and the elastic element 3037 is sleeved on the guide post 3034 and is positioned between the compression nut 3035 and the molded surface positioning block 3036.
In the above embodiment, the connector 3032 may specifically be a hollow structure and have a mounting plate, and is fixedly connected to the tool framework main body 301 through the mounting plate, and in order to facilitate the movement of the handle 3033 along the axial direction of the connector 3032, a gap may be formed in the outer wall of the connector 3032 along the axial direction thereof; the elastic element 3037 may specifically be a spring, two ends of the spring are limited by a compression nut 3035 and a profile positioning block 3036 respectively, and the relative position of the compression nut 3035 on the guide post 3034 is controlled to compress or release 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 cured front and rear skins 202.
Two fixing pin holes are generally provided along the axial direction of the guide post 3034 to satisfy two status positions of the profile positioning block 3036 (one is an initial position away from the stringer 201, and the other is a use position of the auxiliary fitting 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 guiding post 3034 through the limiting pin 3038; the limit pin 3038 is inserted into the guide post 3034 and the profile positioning block 3036 in sequence and can move along 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 connecting piece 3032 by the limit pin 3038.
As an alternative embodiment, as shown in fig. 6 to 7, the profile positioning block 3036 is provided with a kidney-shaped hole. The slotted hole can allow the profile positioning block 3036 to move axially relative to the guide post 3034, so that the compression degree of the profile positioning block 3036 on the stringer 201 can be properly adjusted.
As an alternative embodiment, the inner profile of the profile holder 3036 is adapted to the theoretical outer profile of the stringer 201. Wherein, can make profile locating piece 3036 can laminate more with stringer 201 like this, ensure that location in-process stringer 201 is more stable, do not take place to squint.
As an alternative embodiment, there is a clearance between the inner profile of the profile positioning block 3036 and the theoretical outer profile of the stringer 201. The reserved gap is set in order to place the auxiliary assembly 4 on the surface of the stringer 201, and the interval of 0.2 mm-0.5 mm is reserved in consideration of the requirements of the thickness of the auxiliary material and the positioning accuracy of the molded surface.
The auxiliary component 4 is a general name of a vacuum auxiliary material essential in the composite material forming process, mainly comprises a vacuum bag film, an isolation film, an air-permeable felt, a peelable cloth and the like, and is used for completely covering and adhering 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 wallboard, which comprises the following steps:
s100, mounting a plurality of groups of stringer positioning snap-gauge boards 3 on the positioning section of the wallboard forming tool 1, and enabling the positioning compression assembly 303 of each stringer positioning snap-gauge board 3 to be located at an initial position far away from the stringer 201 and fixed;
s200, installing each stringer 201 on the reinforced wall plate 2, pressing the gluing 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 that the stringer positioning clamping plate is attached to the auxiliary assembly 4 and fixed;
s400, sequentially positioning each stringer 201, packaging the end parts, and curing;
s500, after the solidification is finished, all the positioning compression assemblies 303 are controlled to move to initial positions far away from the stringer 201 and fixed, and the stringer positioning clamping plates 3 are adjusted away.
In the above embodiment, in step S100, a plurality of sets of stringer positioning snap-gauge boards are installed on the positioning section of the panel forming tool by using a traveling crane, and the moving handle is controlled to make the moving parts of the positioning and pressing assemblies of all the stringer positioning snap-gauge boards be at the initial positions far away from the molded surface, and the moving parts are fixed by using the fixing pins.
In step S200, an operator mounts each glued stringer from the top of the radian to the bottom of the radian according to the projected reticle of the laser positioning instrument or the end positioner, presses the glued joint of the stringers after each stringer is placed, and places an auxiliary material on each stringer.
In step S300, the motion handle is controlled to move the motion part of the positioning and pressing assembly of the plurality of sets of stringer positioning tools corresponding to the stringers on which the auxiliary material is placed to the final use position, the guide post is moved to the final use position and fixed by using the fixing pin, and the pressing nut is adjusted to enable the profile positioning block to have a certain pressing force, so that the profile of the profile positioning block is attached to the auxiliary material on the outer side of the stringers.
In step S500, after the curing is completed, each moving handle on each group of positioning tools is controlled to move the moving part of the positioning and compressing assembly of all the stringer positioning tools to the initial position far from the molded surface, and the stringer positioning tools are adjusted and separated by using the traveling crane and fixed by using the fixing pins.
It should be clear that the embodiments in this specification are described in a progressive manner, and the same or similar parts in the embodiments are referred to each other, and each embodiment focuses on the differences from the other embodiments. The present invention is not limited to the specific steps and structures described above and shown in the drawings. Also, a detailed description of known process techniques is omitted herein for the sake of brevity.
The above are merely examples of the present application and are not intended to limit the present application. Various modifications and alterations to this application will become apparent to those skilled in the art without departing from the scope of this invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the scope of the claims of the present application.
Claims (10)
1. The stringer positioning tool for manufacturing the composite 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 a wallboard forming tool (1) and positioning stringers (201) in a stiffened wallboard (2); wherein,
the stringer positioning clamping plate (3) comprises a tool framework main body (301), a connecting positioning assembly (302) and a positioning pressing assembly (303), and two ends of the tool framework main body (301) are fixedly connected with the wallboard forming tool (1) through the connecting positioning assembly (302); a plurality of location compresses tightly subassembly (303) and follows the span direction of frock skeleton main part (301) sets up and be used for the stringer (201) of the corresponding cross-section position of location at interval in proper order.
2. The stringer positioning tool for manufacturing composite fuselage panels as claimed in claim 1, wherein the bases on both sides of the tool skeleton body (301) are provided with limiting round holes for positioning with the connecting and positioning assembly (302).
3. The stringer positioning tooling for composite fuselage panel fabrication of claim 1, the connecting and 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 backing plate (3022) and the fixing nut (3023) are arranged on platforms at two sides of the wallboard 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 the butt joint surface of the side platform of the wallboard forming tool (1), the first fixing bolt (3024) is located on two sides of the guide pin shaft (3021) and is used for fixedly connecting the tool framework main body (301) and the wallboard forming tool (1).
4. The stringer positioning tooling for manufacturing a composite fuselage panel of claim 1 wherein said positioning hold-down assembly (303) comprises a fixed portion and a moving portion; the one end of fixed part install in the lower extreme of frock skeleton main part (301), the motion portion is located the other end of fixed part just is used for carrying out elastic positioning to stringer (201).
5. The stringer positioning tool for manufacturing composite fuselage panels according to claim 4, wherein the fixed portion comprises a fixed pin (3031) and a connector (3032), and the moving portion 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 column (3034) and used for being connected with the tool framework main body (301), the profile positioning block (3036) is movably connected to the second end of the guide column (3034), the guide column (3034) is provided with a plurality of fixing pin holes matched with the fixing pins (3031) along the axial direction of the guide column, and the moving handle (3033) is fixedly connected with the guide column (3034) and used for driving the guide column (3034) to move along the axial direction of the connecting piece (3032);
the compression nut (3035) is in threaded connection with the guide column (3034), and the elastic element (3037) is sleeved on the guide column (3034) and is located between the compression nut (3035) and the molded surface positioning block (3036).
6. The stringer positioning tooling for manufacturing a composite fuselage panel of claim 5, wherein the moving portion further comprises a limit pin (3038), and the profile positioning block (3036) is movably connected to the guide post (3034) through the limit pin (3038);
the limiting pin (3038) is sequentially inserted into the guide post (3034) and the molded surface positioning block (3036) and can move along the axial direction of the guide post (3034).
7. The stringer positioning tooling for manufacturing composite fuselage panels of claim 6, wherein the limiting pin holes provided on the profile positioning blocks (3036) are kidney-shaped holes.
8. The stringer positioning tooling for composite fuselage panel fabrication of claim 5 wherein the inner profile of the profile positioning block (3036) is adapted to the theoretical outer profile of the stringer (201).
9. The stringer positioning tooling for manufacturing a composite fuselage panel of claim 8, wherein a clearance is provided between the inner profile of the profile positioning block (3036) and the theoretical outer profile of the stringer (201).
10. A use method of a stringer positioning tool for manufacturing a composite material fuselage panel is characterized by comprising the following steps of:
1) installing a plurality of groups of stringer positioning clamping plates (3) on a positioning section of a wallboard forming tool (1), and enabling a positioning pressing assembly (303) of each stringer positioning clamping plate (3) to be located at an initial position far away from a stringer (201) and fixed;
2) after each stringer (201) is installed on the reinforced wallboard (2), the adhesive joint surface of the stringer (201) is pressed, and an auxiliary assembly (4) is placed 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 that the positioning and pressing assembly fits the auxiliary assembly (4) and is fixed;
4) sequentially positioning each stringer (201), packaging the end parts, and curing;
5) and after the solidification is finished, controlling all the positioning and pressing assemblies (303) to move to the initial positions far away from the stringer (201) and fixing, and adjusting away the stringer positioning clamping plates (3).
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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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