CN204566716U - The accurate forming frock of aircraft composite - Google Patents

Abstract

The utility model relates to the accurate forming frock of a kind of aircraft composite, for in aircraft composite material shaping process, affect the many factors of its dimensional accuracy, and Influencing Mechanism is complicated, as mold materials and structure, composite plys angle, the number of plies and curing process etc., and aircraft composite belongs to the production of single-piece large piece with manufacture composite frock, the deformation rule of composite material parts cannot be obtained by batch production, the utility model provides a set of test piece and prepares particular manufacturing craft, test piece, operating desk base, simple forming mould, shell mould, the accurate forming frock of aircraft composite of the composition such as filler, test piece is prepared by preparing on particular manufacturing craft in test piece, and obtain data correction product digital-to-analogue, forming errors can be compensated, simple forming mould makes shell die face, thus effectively reduce mold hot capacity, be conducive to optimizing curing reaction, again reduce die manufacturing cost, improve product quality.

Description

The accurate forming frock of aircraft composite

Technical field

The utility model relates to the accurate forming frock of a kind of aircraft composite.

Background technology

Present stage, forming method many employings solidification of hot-press tank of composite material parts was shaping, and its manufacture process is generally and manufactures and designs mould according to product data model; Recycle this Making mold composite products.According to this technique, the precision quality of composite product depends on precision quality and the thermoforming feature of composite own of mould to a great extent, and due in composite material shaping process, affect the many factors of its precision, if there is no corresponding data supporting during designing mould, be difficult to appropriate design die face, composite products and original digital-to-analogue is caused to there is comparatively big error, affect it to use, and the production of aircraft belongs to large piece single-piece production, the deformation rule of composite material parts cannot be obtained by batch production, and manufacture composite material parts frock and also belong to large piece single-piece production, also cannot obtain by batch production the deformation rule that composite material forming is affected, therefore, present stage Making mold and composite product production process in, the impact of these factors on part accuracy is not well solved, have impact on composite product precision.

Summary of the invention

Technical problem to be solved in the utility model is in aircraft composite material shaping process, affect the many factors of its dimensional accuracy, and Influencing Mechanism is complicated, as mold materials and structure, multiple material laying angle, the number of plies and curing process etc., and aircraft composite all belongs to large piece single-piece production with manufacture composite frock, the deformation rule of composite material parts cannot be obtained by batch production, therefore, present stage Making mold and composite material parts production process in, the impact of these factors on element precision is not well solved, have impact on the composite material parts accuracy of manufacture, the utility model provides the accurate shaping fabricating tools of a kind of aircraft composite, by test piece data correction product digital-to-analogue, the deflection of composite product manufacture process can be compensated, adopt shell die face again, effectively reduce again mold hot capacity, be conducive to optimizing curing reaction, again reduce die manufacturing cost, improve composite products dimensional accuracy, reach precisely shaping object.

The utility model solves the technical scheme that its technical problem adopts:

The accurate forming frock of a kind of composite, particular manufacturing craft (1) is prepared by test piece, composite test piece (2), operating desk base (3), simple forming mould (4), shell mould (5), filler (4-12) forms, it is characterized in that: particular manufacturing craft (1) and operating desk base (3) rigid attachment are prepared in described test piece, test piece prepares the profile of particular manufacturing craft (1) by convex arc surface, concaved circular cambered surface, gradient face, plane forms, the concrete profile that particular manufacturing craft (1) is prepared in test piece requires preparation according to all composite material parts data models, the parameter such as laying angle, the number of plies, curing process of described composite test piece (2) is consistent with needing the initial data of the composite product data model prepared, all identical with the composite material parts needing to prepare, to ensure the similitude of test piece and composite product, described simple forming mould (4) forms also each other rigid attachment to gusset (4-1), V to gusset (4-2), mold base (4-3) and technique earhole base (4-4) by U, U forms latticed rigid attachment with V to gusset (4-2) to gusset (4-1), U welds rigid attachment with mold base (4-3) to gusset (4-1) and V respectively to gusset (4-2), inject filler (4-12) in grid groove inside, populated upper surface carries out scratch-type by technique initial data profile, described shell mould (5) profile is determined by the composite product data model needing to prepare, adopt thickness specification to be 10 ~ 12mm sheet material through profile and compensate type of repairing, wrinkling place pre-processed board, material add that heat sealing die is shaping, cooling, repair welding, numerical control polishing fine finishining is shaping and repair type, formation one-tenth-value thickness 1/10 is at least 4mm shell frock.

Accompanying drawing explanation

Fig. 1 is that particular manufacturing craft schematic diagram is prepared in test piece of the present utility model.

Fig. 2 be simple forming mould structure schematic diagram of the present utility model (wherein, Fig. 2-1 is simple forming mould structure schematic diagram of the present utility model, Fig. 2-2 is network schematic diagrames of weld connection mode of the present utility model, and Fig. 2-3 is network schematic diagrames of insertion connecting mode of the present utility model).

Fig. 3 be shell mould structure schematic diagram of the present utility model (wherein, Fig. 3-1 is shell mould structure schematic diagram of the present utility model, Fig. 3-2 is pad pasting test schematic diagrames on simple die of the present utility model, Fig. 3-3 is cutting process schematic diagrames that shell die face raw material of the present utility model play fold place, and Fig. 3-4 is the shaping schematic diagrames of matched moulds of the present utility model).

Particular manufacturing craft is prepared in 1-test piece, the test piece of 2-composite, 3-operating desk base, 4-simple forming mould, 4-1-U is to gusset, 4-2-V is to gusset, 4-3-mold base, 4-4-technique earhole base, 4-5-convex profile, 4-6-supporter, 4-7-slots, 4-8-convex profile, 4-9-supporter, 4-10-slots, 4-11-grid dead slot, 4-12-filler, 4-13-technique earhole seat supports body, 4-14-technology hole, 5-shell mould, 5-1-Polypropylence Sheet, 5-2-plays fold place, 5-3-has removed the shell base mould material at fold position, 5-4-cutting process plays the otch gap at fold place, 5-5-die, 5-6-punch.

Detailed description of the invention

The technical program can also be realized by following technical measures and the invention will be further described below in conjunction with accompanying drawing:

Fig. 1 is that particular manufacturing craft schematic diagram is prepared in test piece of the present utility model, particular manufacturing craft (1), composite test piece (2), operating desk base (3) composition is prepared primarily of test piece, it is characterized in that: particular manufacturing craft (1) and operating desk base (3) rigid attachment are prepared in described test piece, the profile that particular manufacturing craft (1) is prepared in test piece is made up of convex arc surface, concaved circular cambered surface, gradient face, plane, and the concrete data model of profile that particular manufacturing craft (1) is prepared in test piece is determined by the requirement of all composite material parts; The parameter such as laying angle, the number of plies, curing process of described composite material parts test piece (2) is consistent with needing the initial data of the composite product data model prepared, all identical with the composite product needing to manufacture, to ensure the similitude of test piece and composite product.

Fig. 2 be simple forming mould structure schematic diagram of the present utility model (wherein, Fig. 2-1 is simple forming mould structure schematic diagram of the present utility model, Fig. 2-2 is network schematic diagrames of weld connection mode of the present utility model, Fig. 2-3 is network schematic diagrames of insertion connecting mode of the present utility model), primarily of U to gusset (4-1), V is to gusset (4-2), mold base (4-3), technique earhole base (4-4), convex profile (4-5), supporter (4-6), fluting (4-7), convex profile (4-8), supporter (4-9), fluting (4-10), grid dead slot (4-11), filler (4-12), technique earhole seat supports body (4-13), technology hole (4-14) forms, and it is characterized in that: primarily of U to gusset (4-1), V is to gusset (4-2), mold base (4-3) forms a latticed low cost simple mould, material therefor is common iron, adopt the grid of equal spacing distance, the size of space is the interval of 200 ~ 300mm, number of grid is determined by composite gauge, filler (4-12) is injected between grid dead slot (4-11) between each grid of mould, filler (4-12) generally selects cement as filler, for raising and the quick heat radiating of mould strength, and populated upper surface is carried out scratch-type by die face, described technique earhole base (4-4) is made up of technique earhole seat supports body (4-13) and technology hole (4-14), technology hole (4-14) is for the resetting of numerical control amend mould, and technique earhole base (4-4) adopts welding manner rigid attachment at the outermost U of mould to gusset (4-1) or V on gusset (4-2), described U adopts welding manner and mold base (4-3) rigid attachment to gusset (4-1) or V respectively to gusset (4-2), described U all adopts two kind structures with V to gusset (4-2) to gusset (4-1), two kinds of structures that U adopts to gusset (4-1), a kind of is to gusset (4-1) without the U slotted, another kind of structure has the U of fluting (4-7) to gusset (4-1), wherein, U without fluting forms to gusset primarily of convex profile (4-5), supporter (4-6), and has the U of fluting (4-7) to gusset primarily of convex profile (4-5), supporter (4-6), fluting (4-7) composition, two kinds of structures that V adopts to gusset (4-2), a kind of is to gusset (4-2) without the V slotted, another kind of structure has the V of fluting (4-10) to gusset (4-2), wherein, V without fluting mainly contains convex profile (4-8), supporter (4-9) composition to gusset (4-2), and has the V of fluting (4-10) to mainly contain convex profile (4-8), supporter (4-9), fluting (4-10) composition to gusset (4-2), described U is consistent with the Mathematical Modeling of the relevant position structure of composite material parts respectively to the convex profile (4-8) of gusset (4-2) with V to the convex profile (4-5) of gusset (4-1), shaping by laser cutting, described U adopts to gusset (4-1) and V to gusset (4-2) and to weld or the rigid attachment of inserted mode forms latticed, to match to gusset (4-1) and the V that slots of nothing to gusset (4-2) without the U of fluting and adopt welding manner rigid attachment, have the U of fluting (4-7) to gusset (4-1) with have the V of fluting (4-10) to match to gusset (4-2) to adopt the rigid attachment of inserted mode, operating procedure is as follows: adopt common iron to add through laser cutting and obtain contour shape, fenestral fabric is formed through welding again using it as gusset, and make its upper surface consistent with required shell die face, size of mesh opening is designed to 200 ~ 300mm, grid inside is filled with filler, and populated upper surface is carried out scratch-type by technique digital-to-analogue profile.

Fig. 3 be shell mould structure schematic diagram of the present utility model (wherein, Fig. 3-1 is shell mould structure schematic diagram of the present utility model, Fig. 3-2 is pad pasting test schematic diagrames on simple die of the present utility model, Fig. 3-3 is cutting process schematic diagrames that shell die face raw material of the present utility model play fold place, Fig. 3-4 is the shaping schematic diagrames of matched moulds of the present utility model), primarily of Polypropylence Sheet (5-1), play fold place (5-2), remove the shell base mould material (5-3) at fold position, cutting process plays the otch gap (5-4) at fold place, die (5-5), punch (5-6) forms, operating procedure is as follows: (1) chooses the material specification for the manufacture of die face, according to die needed profile size, select the sheet material of suitable flat size, thickness specification elects 10 ~ 12mm as, (2) according to the thermal coefficient of expansion of mold materials, process is compensated to composite material mould profile, concrete way carries out scale amplifying to composite material mould profile by the thermal coefficient of expansion of mold materials, obtain the profile of simple die, the ratio of amplifying is Δ L, the expression formula of Δ L is Δ L=1+ β × Δ T, and wherein β is the thermal coefficient of expansion of mold materials, and Δ T is the difference of forming temperature and room temperature, to the cutting process playing fold place in sheet material heat forming processes, in order to reduce tension-thining and wrinkling, therefore need to anticipate the part of wrinkling windrow, remove unnecessary material, for this reason, before the forming, first adopt the mode of Polypropylence Sheet pad pasting in simple die profile of existing sheet material same size to find out fold position and dimensional parameters, selected sheet material raw material is removed unnecessary material by the corresponding site cutting playing fold of Polypropylence Sheet, (3) carry out sheet material heating at coreless induction furnace, wrinkling pretreated plate is put into dielectric heating oven, to its heating that heats up after requiring the setting parameter such as heating-up temperature and time according to the concrete shaping difference of mould, (4) taken out by dielectric heating oven by the sheet material after heating, be placed on simple die, matched moulds pressurization is fixing, and itself and die face are fitted, (5) matched moulds is shaping reduces to after normal value until temperature, opens mould, take out shaping after material, the gap that pretreatment cutting part is formed is welded, (6) the die face blank after welding carried out to numerical control polishing fine finishining and repaiies type, ensureing that shaping rear mold one-tenth-value thickness 1/10 is at least 4mm, being the shell mould of final required profile.

Claims (1)

1. the accurate forming frock of aircraft composite, particular manufacturing craft (1) is prepared by test piece, composite test piece (2), operating desk base (3), simple forming mould (4), shell mould (5), filler (4-12) forms, it is characterized in that: particular manufacturing craft (1) and operating desk base (3) rigid attachment are prepared in described test piece, test piece prepares the profile of particular manufacturing craft (1) by convex arc surface, concaved circular cambered surface, gradient face, plane forms, the concrete profile that particular manufacturing craft (1) is prepared in test piece requires preparation according to the profile of all composite material parts data models, the parameter such as laying angle, the number of plies, curing process of described composite test piece (2) is consistent with needing the initial data of the composite product data model prepared, all identical with the composite product needing to prepare, to ensure the similitude of test piece and composite product, described simple forming mould (4) forms also each other rigid attachment to gusset (4-1), V to gusset (4-2), mold base (4-3) and technique earhole base (4-4) by U, U forms latticed rigid attachment with V to gusset (4-2) to gusset (4-1), U welds rigid attachment with mold base (4-3) to gusset (4-1) and V respectively to gusset (4-2), inject filler (4-12) in grid groove inside, populated upper surface carries out scratch-type by technique initial data profile, the profile of described shell mould (5) is determined by the composite product data model needing to prepare, adopt thickness specification to be 10 ~ 12mm sheet material through profile and compensate type of repairing, the pretreatment of wrinkling place, sheet material add that heat sealing die is shaping, cooling, repair welding, numerical control polishing fine finishining is shaping and repair type, formation one-tenth-value thickness 1/10 is at least 4mm shell frock.