CN106626434B - A kind of manufacture of technique for aircraft composite bulkhead structure and design method - Google Patents
A kind of manufacture of technique for aircraft composite bulkhead structure and design method Download PDFInfo
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- CN106626434B CN106626434B CN201611177437.8A CN201611177437A CN106626434B CN 106626434 B CN106626434 B CN 106626434B CN 201611177437 A CN201611177437 A CN 201611177437A CN 106626434 B CN106626434 B CN 106626434B
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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
-
- 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
-
- 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
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The present invention relates to a kind of design of technique for aircraft composite bulkhead structure and manufacturing methods, including S10: determining the design requirement of the composite material bulkhead;S20: the configuration, material and process program of technique for aircraft composite bulkhead are determined according to the design requirement;S30: the composite material bulkhead modeling and analysis.Technique for aircraft composite bulkhead structure manufacture of the invention and design method can ground and the development of in-service civil aircraft fuselage composite material bulkhead structure provides technical support for China, reduce construction weight, aeroplane performance is promoted, working service cost is reduced, increases economic efficiency.
Description
Technical field
The invention belongs to technical field of aircraft structure design more particularly to a kind of technique for aircraft composite bulkhead structure production and
Design method.
Background technique
It is well known that in airplane design, composite material is high, corrosion-resistant, antifatigue etc. excellent with its specific stiffness/specific strength
Performance is more and more widely used in aircaft configuration.Composite material can effectively reduce aero-structure weight, and it is commercial to improve aircraft
Load;Or increase amount of fuel, improve aircraft range.On the other hand, the application of composite material can reduce aircaft configuration inspection time
Number improves inspection intervals, reduces aircraft maintenance cost, to fundamentally improve civil aircraft in entire service life service phase
Economic benefit.
External advanced civil aircraft such as Air Passenger A350 and Boeing B787 wait aircrafts, and composite material dosage has accounted for aircaft configuration
50% or more of weight, position include fuselage, wing, empennage covering, fuselage bulkhead, joist, floor pillar, side of a ship window frame,
The structures such as wing spar, rib.Along with Project R&D, formd complete set Aircraft Composite Structure design and
The method and process of manufacture.
In domestic some aircaft configurations in-service at present, 90% or more is all aluminium alloy, and composite material dosage is few, and
It applies in secondary load-carrying construction, there is no the experience of aircraft main force support structure application composite material, more lack multiple material structure design point
The method of analysis manufacture and verifying.Therefore, carry out application technical research of the composite material in civil aircraft structures, be that raising China is civilian
The important means of aeroplane performance and the market competitiveness.
Summary of the invention
The object of the present invention is to provide the designs and manufacturing method of a kind of airframe composite material bulkhead structure, promote me
The technical level of its people's aircaft configuration application composite material, provides for the improvement of China's developing model and the remodeling of in-service model
Technical support.
In order to achieve the above objectives, the technical solution adopted by the present invention is that: a kind of technique for aircraft composite bulkhead structure design side
Method, including
S10: the design requirement of the composite material bulkhead is determined
The design requirement include aircraft total arrangement and basic parameter, design load, material and technology requirement, using dimension
Protect requirement, integrity demands, weight demands, cost requirement;
S20: the configuration, material and process program of technique for aircraft composite bulkhead are determined according to the design requirement
The shear band that is configured as of the technique for aircraft composite bulkhead floats the configuration that frame combines with " C " shape, and prepreg uses
Carbon fibre fabric, forming technology is using manual laying and hot pressing can shaping;
S30: the composite material bulkhead modeling and analysis
Determine composite material bulkhead structure: the edge strip of the composite material bulkhead strains under drawing/pressure ultimate load to be less than
Permissible, and the edge strip not unstability under compression limit load;Web is strained in the case where shearing ultimate load is less than permissible, and
Do not generate shearing instability;
Composite material bulkhead parametric modeling, and model is optimized.
Further, the total arrangement and basic parameter include fuselage cross-section size, fuselage skin and bulkhead piecemeal
And segmentation requires;
The design load include fuselage overall tensile, compression, bending, shearing, torsional load, CAB PRFS load and
The stacking method of above-mentioned several load;
The integrity demands include the selection of rigidity/intensity requirement, fatigue and damage tolerance requirements, design margin evaluation
And the special bearing requirements of airframe structure as defined in seaworthiness.
A kind of technique for aircraft composite bulkhead structure manufacturing method is additionally provided, shear band is combined with " C " shape mansion frame
Composite material bulkhead is manufactured, including
Design and produce the tooling of the composite material bulkhead;The tooling includes part, solidification plate, movable core model, consolidates
Determine core model, active block stop and;
The fixed core model is segmented in the longitudinal direction, and is equipped with and is stuck up mouth, for demoulding;Movable core model is used for part
The paving and pressurization of stile;Fixed core model is equipped with step, and for limiting thickness, the step height is the lower difference of part thickness;Top
The inside C-shaped blank consolidation that tight device is used to complete paving presses;
Determine process flow: the process flow include prepare pressure equalizing cover plate, part paving combination, package curing, demoulding,
Machine adds blanking and quality examination.
Further, the solidification plate, core model, active block stop and pre-tightening apparatus are all made of metal material and are made.
It is further, described to prepare pressure equalizing cover plate process are as follows:
Pressure equalizing cover plate need to be manufactured according to piece surface flatness requirement after part curvature and encapsulation;It is mother with forming frock
Mould, using the process conditions of the paving of glass fibre prepreg, solidification and part equal thickness, after shape is corrected, outside process conditions
The compound pressure equalizing cover plate of rubber of surface paving, encapsulation, cured fiber enhancing, the guarantee for part outer surface type face.
Further, the part paving anabolic process are as follows:
It by two groups of inside C-shaped blank consolidation pavings to movable core model and is fixed on core model, C-shaped blank according to laying table respectively
Paving goes out crimp at single side surplus, calculates the loading of the angle R filler and makes the angle R using the dedicated angle R filler shaping dies
The movable core model of paving part blank and fixed core model are close to holding device, and are sealed in room temperature using vacuum bag by filler
Dress compacting, so that two groups of inside C-shaped blanks fit closely, according to C-shaped blank outside the paving of laying angle requirement, external C-shaped base
Expect crimp at the paving of two sides, the compacting of vacuum bag encapsulation twice, it is ensured that the size and location relationship of each section blank.
Further, the package curing process are as follows:
Removal holding device places auxiliary material and pressure equalizing cover plate by process sequence, and encapsulation is to solidification plate, into autoclave
Solidification.
Further, the knockout course are as follows:
Vacuum bag, pressure equalizing cover plate and corresponding auxiliary material are removed, agitates sled mouth position twice, root simultaneously using extractor
It is demoulded according to mould separating sequence;After agitating, part is invested on movable core model and active block stop, and is detached from fixed core model,
Part is separated with movable core model, active block stop again.
Further, the machine adds blanking process are as follows:
Machine is carried out according to part edge line and adds blanking, part surplus is removed, according to heat of the tooling material in solidification temperature
Carry out blanking of the difference of the coefficient of expansion and part thermal expansion coefficient to part edge line itself.
Further, the quality inspection processes are as follows:
By the way that part is back to molding die inspection and corresponding size detection, spare part outside measurement measurement is qualified, ultrasound
Non-destructive testing is qualified, voidage test passes, and presentation quality is good.
Technique for aircraft composite bulkhead structure manufacture of the invention and design method can ground and in-service civil aircraft for China
The development of fuselage composite material bulkhead structure provides technical support, reduces construction weight, promotes aeroplane performance, reduces working service
Cost is increased economic efficiency.
Detailed description of the invention
The drawings herein are incorporated into the specification and forms part of this specification, and shows and meets implementation of the invention
Example, and be used to explain the principle of the present invention together with specification.
Fig. 1 is fuselage global optimization model of the invention;
Fig. 2 is bulkhead structure details finite element model of the invention;
Fig. 3 is bulkhead shaping dies schematic diagram of the invention.
Specific embodiment
To keep the purposes, technical schemes and advantages of the invention implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.Embodiment below with reference to attached drawing description is exemplary type, it is intended to be used
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's every other embodiment obtained under the premise of not making the labour of creation type, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention in conjunction with attached drawing.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the present invention
The limitation of range.
One, technique for aircraft composite bulkhead structure designs
1, technique for aircraft composite bulkhead structure design requirement
1.1) total arrangement and basic parameter: including fuselage cross-section size, fuselage skin and bulkhead piecemeal and segmentation feelings
Condition;
1.2) design load: including fuselage overall tensile, compression, bending, shearing, torsional load, CAB PRFS load with
And the stacking method of above-mentioned several load;
1.3) material and technology requirement: pressing airworthiness requirement, the manufactures of civil aircraft components need to using mature material and
Manufacturing process, and selected material and manufacturing process need to be by approved MAT'L specification and technological specification to guarantee product matter
Amount;
1.4) working service requirement: the convenience for using and safeguarding during being on active service including aircraft;
1.5) integrity demands: the choosing including rigidity/intensity requirement, fatigue and damage tolerance requirements, design margin evaluation
Take and seaworthiness as defined in the special bearing requirements of airframe structure;
1.6 weight demands: including component weight control and loss of weight requirement;
1.7 cost requirements: including in design and analysis, manufacture, test, use, entire military service period for safeguarding and scrapping
Cost control requirement.
2, technique for aircraft composite bulkhead structure configuration, material and process program are chosen
According to common fuselage bulkhead cross sectional configuration, external advanced civil aircraft fuselage composite material bulkhead configuration (see attached drawing 1)
And it is domestic at present using more mature prepreg and forming technology, determine the configuration that frame is floated using shear band+" C " shape, preimpregnation
Material uses II carbon fibre fabric of CF3052/BA9916-, the method that forming technology uses manual laying+hot pressing can shaping.
3, the detailed design of technique for aircraft composite bulkhead structure and analysis
3.1) determine bulkhead structure design criteria: edge strip strains under drawing/pressure ultimate load is less than permissible, and is pressing
Edge strip not unstability under contracting ultimate load;Web is strained in the case where shearing ultimate load is less than permissible, and does not generate shearing instability;
3.2) structure parameterization models, and carries out parameter Optimization Analysis to overall model (see attached drawing 2);
3.3) CONSTRUCTED SPECIFICATION models in detail, checks bulkhead entirety and local load is horizontal, check securing member intensity (see
Attached drawing 3);
3.4) adjustment local detail design based on the analysis results, meets Structural Design Requirement.
Two, technique for aircraft composite bulkhead structure manufactures
1, part forming Fixture Design: including part 1, solidification plate 2, movable core model 3, fixed core model 4, active block stop 5
And pre-tightening apparatus 6;
Core model is segmented in the longitudinal direction, and every section design it is appropriate stick up mouth, convenient for demoulding.Movable core model
Design is the paving and pressurization for the ease of part stile.
Step on fixed core model is limited thick step, and step height is the lower difference of part thickness, and it acts as prevent center
Stile is excessively thin, prevents central stile from cannot pressurize, playing a supportive role to part stile, and the prevention angle R is excessively thin.
Wherein solidify plate, core model, active block stop and pre-tightening apparatus and is all made of metal material, metal forming die surface light
Cleanliness is good, and size Control is superior, service life is permanent.The inside C-shaped blank consolidation that holding device can complete paving presses, then
It will be filled using the angle the R filler of the dedicated angle R filler shaping dies production to corresponding position, under holding device effect outside paving
C-shaped blank.Movable core model and active block stop length direction uniformly prize mouth, and mold agitates when for demoulding, blank paving to work
At dynamic core model flange and active block stop, so that part stress is uniform when demoulding agitates.Most external can increase fibre-reinforced rubber
Compound pressure equalizing cover plate, can uniformly compression of the part in autoclave, guarantee accessory appearance quality.
2, determine process flow: including preparing pressure equalizing cover plate, part paving combination, package curing, demoulding, machine add blanking and
Quality examination.
Although fuselage bulkhead design of part form is simple, since part curvature is big, auxiliary material cannot when cure package
Regular is packaged in piece surface, it cannot be guaranteed that the surface quality of part, therefore pressure equalizing cover plate need to be manufactured.It is mother with forming frock
Mould is selected the process conditions of the paving of glass fibre prepreg, the solidification and part equal thickness of advantage of lower cost, is corrected by shape
Afterwards, in the compound pressure equalizing cover plate of rubber of the paving of process conditions outer surface, encapsulation, cured fiber enhancing, it is used for part outer surface type face
Guarantee.Due to the sub-assembly that bulkhead is two C-shaped parts, 0 ° of fiber need to be filled in combination zone, but filling region surface is easy
Protrusion is generated, therefore increases the rigidity of 0 ° of fiber filling region in the production of pressure equalizing cover plate.
C-shaped is paid attention in two groups of inside C-shaped blank consolidation pavings to movable core model and fixed core model according to laying table respectively
Blank paving at single side surplus goes out crimp, calculates the loading of the angle R filler and is made of the dedicated angle R filler shaping dies
The angle R filler.The movable core model of paving part blank and fixed core model are close under the action of holding device, and adopted in room temperature
It is encapsulated and is compacted with vacuum bag, so that two groups of inside C-shaped blanks fit closely.The angle R filler is placed in accurate location, according to laying
C-shaped blank outside angle requirement paving.Crimp at the two sides paving of external C-shaped blank, the compacting of vacuum bag encapsulation twice, it is ensured that each portion
Divide the size and location relationship of blank.
Removal holding device places corresponding auxiliary material and pressure equalizing cover plate by process sequence, and encapsulation is to solidification plate, into heat
Press tank solidification.
Vacuum bag, pressure equalizing cover plate and corresponding auxiliary material are removed, agitates sled mouth position twice, root simultaneously using extractor
It is demoulded according to mould separating sequence.After agitating, part is invested on movable core model and active block stop, and is detached from fixed core model,
Part is separated with movable core model, active block stop again.
Machine is carried out according to part edge line and adds blanking, removes part surplus.Consider tooling material in solidification temperature before blanking
When thermal expansion coefficient and part thermal expansion coefficient itself influence of the difference to part edge line.
By the way that part is back to molding die inspection and corresponding size detection, spare part outside measurement measurement is qualified, ultrasound
Non-destructive testing is qualified, voidage test passes, and presentation quality is good.
The of the invention design of technique for aircraft composite bulkhead structure and manufacturing method can ground and in-service civil aircraft for China
The development of fuselage composite material bulkhead structure provides technical support, reduces construction weight, promotes aeroplane performance, reduces working service
Cost is increased economic efficiency.
The above, optimal specific embodiment only of the invention, but scope of protection of the present invention is not limited thereto,
In the technical scope disclosed by the present invention, any changes or substitutions that can be easily thought of by anyone skilled in the art,
It should be covered by the protection scope of the present invention.Therefore, protection scope of the present invention should be with the protection model of the claim
Subject to enclosing.
Claims (5)
1. a kind of technique for aircraft composite bulkhead structure manufacturing method, which is characterized in that mutually tied for floating frame with " C " shape to shear band
The composite material bulkhead of conjunction is manufactured, including
Design and produce the tooling of the composite material bulkhead;The tooling includes part, solidification plate, movable core model, fixed core
Mould, active block stop;
The fixed core model is segmented in the longitudinal direction, and is equipped with and is stuck up mouth, for demoulding;Movable core model is used for part stile
Paving and pressurization;Fixed core model is equipped with step, and for limiting thickness, the step height is the lower difference of part thickness;Hold out against dress
Set the inside C-shaped blank consolidation pressing for completing paving;
Determine that process flow, the process flow include
It prepares pressure equalizing cover plate: pressure equalizing cover plate need to be manufactured according to piece surface flatness requirement after part curvature and encapsulation;With molding
Tooling is master mold, using the process conditions of the paving of glass fibre prepreg, solidification and part equal thickness, after shape is corrected,
The compound pressure equalizing cover plate of rubber of the paving of process conditions outer surface, encapsulation, cured fiber enhancing, the guarantor for part outer surface type face
Card;
Part paving combination: core model by two groups of inside C-shaped blank consolidation pavings to movable core model and is fixed according to laying table respectively
On, the paving at single side surplus of C-shaped blank goes out crimp, calculates the loading of the angle R filler and uses the dedicated angle R filler finishing die
The movable core model of paving part blank and fixed core model are close to holding device, and used in room temperature by the tool production angle R filler
Vacuum bag encapsulation compacting, so that two groups of inside C-shaped blanks fit closely, according to C-shaped blank outside the paving of laying angle requirement, outside
Crimp at portion's C-shaped blank two sides paving, the compacting of vacuum bag encapsulation twice, it is ensured that the size and location relationship of each section blank;
Package curing: removal holding device places auxiliary material and pressure equalizing cover plate by process sequence, and encapsulation extremely solidifies plate, into
Solidification of hot-press tank;
Demoulding and machine add blanking and quality examination.
2. technique for aircraft composite bulkhead structure manufacturing method according to claim 1, which is characterized in that the solidification is flat
Plate, core model, active block stop and pre-tightening apparatus are all made of metal material and are made.
3. technique for aircraft composite bulkhead structure manufacturing method according to claim 2, which is characterized in that the knockout course
Are as follows:
Vacuum bag, pressure equalizing cover plate and corresponding auxiliary material are removed, sled mouth position twice is agitated simultaneously using extractor, according to mould
Tool disengaging sequence is demoulded;After agitating, part is invested on movable core model and active block stop, and is detached from fixed core model, then will
Part is separated with movable core model, active block stop.
4. technique for aircraft composite bulkhead structure manufacturing method according to claim 3, which is characterized in that the machine adds blanking
Process are as follows:
Machine is carried out according to part edge line and adds blanking, part surplus is removed, according to thermal expansion of the tooling material in solidification temperature
Carry out blanking of the difference of coefficient and part thermal expansion coefficient to part edge line itself.
5. technique for aircraft composite bulkhead structure manufacturing method according to claim 4, which is characterized in that the quality examination
Process are as follows:
By the way that part is back to molding die inspection and corresponding size detection, spare part outside measurement measurement is qualified, ultrasonic non-destructive
Detection is qualified, voidage test passes, and presentation quality is good.
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