CN106626434A - Method for manufacturing and designing composite material bulkhead structure of airplane - Google Patents
Method for manufacturing and designing composite material bulkhead structure of airplane Download PDFInfo
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- CN106626434A CN106626434A CN201611177437.8A CN201611177437A CN106626434A CN 106626434 A CN106626434 A CN 106626434A CN 201611177437 A CN201611177437 A CN 201611177437A CN 106626434 A CN106626434 A CN 106626434A
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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 invention relates to a method for manufacturing and designing a composite material bulkhead structure of an airplane. The method comprises the following steps of: S10: determining design requirements of a composite material bulkhead; S20: determining the structure, the material and the process scheme of the composite material bulkhead of the airplane according to the design requirements; and S30: modeling and analyzing the composite material bulkhead. The method for manufacturing and designing the composite material bulkhead structure of the airplane can provide technical support of researching the composite material bulkhead structures of the under-research and in-service civil airplanes in China, reduces structure weight, improves airplane performances, reduces using and maintaining cost, and improves economic benefits.
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 make and
Method for designing.
Background technology
It is well known that in airplane design, composite is high, corrosion-resistant, antifatigue etc. excellent with its specific stiffness/specific strength
Performance, is increasingly widely used in aircaft configuration.Composite can effectively reduce aero-structure weight, improve aircraft commercial
Load；Or increase amount of fuel, improve aircraft range.On the other hand, the application of composite can reduce aircaft configuration and check secondary
Number, improves inspection intervals, reduces aircraft maintenance cost, so as to fundamentally improve civil aircraft in whole life-span service phase
Economic benefit.
The external advanced civil aircraft such as aircraft such as Air Passenger A350 and Boeing B787, its composite consumption has accounted for aircaft configuration
More than the 50% 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, defined complete set Aircraft Composite Structure design and
The method and flow process of manufacture.
In domestic some in-service at present aircaft configurations, more than 90% is all aluminium alloy, and composite consumption is few, and
Apply in secondary load-carrying construction, there is no the experience of aircraft main force support structure application composite, more lack multiple material structure design point
Analysis manufacture and the method verified.Therefore, carry out application technical research of the composite in civil aircraft structures, be that raising China is civilian
The important means of aeroplane performance and the market competitiveness.
The content of the invention
It is an object of the invention to provide a kind of design of airframe composite bulkhead structure and manufacture method, lift me
The national technical merit with aircaft configuration application composite, the remodeling of improvement and in-service model for China's developing model is provided
Technical support.
To reach above-mentioned purpose, the technical solution used in the present invention is：A kind of technique for aircraft composite bulkhead structure design side
Method, including
S10：Determine the design requirement of the composite bulkhead
The design requirement includes that overall aircraft layout is required, uses dimension with basic parameter, design load, material and technology
Shield requirement, integrity demands, weight demands, cost requirement；
S20：Configuration, material and the process program of technique for aircraft composite bulkhead are determined according to the design requirement
The technique for aircraft composite bulkhead is configured as configuration of the shear band in combination with the floating frame of " C " shape, and prepreg adopts
Carbon fibre fabric, forming technology is laid and hot pressing can shaping using manual；
S30：The composite bulkhead modeling and analysis
Determine composite bulkhead structure：The edge strip of the composite bulkhead is strained in the case where drawing/pressing ultimate load and is less than
Permissible, and the edge strip not unstability under compression limit load；Web strain under shearing ultimate load is less than permissible, and
Shearing instability is not produced；
Composite bulkhead parametric modeling, and model is optimized.
Further, the total arrangement includes fuselage cross-section size, fuselage skin and bulkhead piecemeal with basic parameter
And segmentation is required；
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 rigidity/intensity requirement, fatigue and damage tolerance requirements, the selection of design margin evaluation
And the special bearing requirements of airframe structure that seaworthiness specifies.
A kind of technique for aircraft composite bulkhead structure manufacture method is additionally provided, to shear band in combination with the frame of " C " shape mansion
Composite bulkhead is manufactured, including
Design and produce the frock of the composite bulkhead；The frock includes part, solidifies flat board, movable core, consolidates
Determine core, active block stop and；
The fixed core is segmented in the longitudinal direction, and is provided with and is stuck up mouth, for the demoulding；Movable core is used for part
The paving and pressurization of stile；Fixed core is provided with step, and for limiting thickness, the shoulder height is the lower difference of part thickness；Top
Tight device is used for the inside C-shaped blank consolidation pressing for completing paving；
Determine technological process：The technological process include prepare pressure equalizing cover plate, part paving combination, package curing, the demoulding,
Machine adds blanking and quality examination.
Further, the solidification flat board, core, active block stop and pre-tightening apparatus are made using metal material.
Further, the pressure equalizing cover plate process for preparing is：
Pressure equalizing cover plate need to be manufactured according to piece surface flatness requirement after part curvature and encapsulation；With forming frock as mother
Mould, using the process conditions of glass fibre prepreg paving, solidification and part equal thickness, after profile amendment, outside process conditions
Surface paving, encapsulation, the enhanced rubber combined pressure equalizing cover plate of cured fiber, for the guarantee in part outer surface type face.
Further, the part paving anabolic process is：
Respectively according to laying table is by two groups of inside C-shaped blank consolidation pavings to movable core and fixes on core, C-shaped blank
The paving at one side surplus goes out crimp, calculates the loading of R angles filler and makes R angles using special R angles filler shaping dies
Filler, is close to the movable core of paving part blank with fixed core with holding device, and is sealed using vacuum bag in room temperature
Dress compacting so that two groups of inside C-shaped blanks are brought into close contact, according to laying angle requirement paving outside C-shaped blank, outside C-shaped base
Crimp at material both sides paving, the compacting of vacuum bag encapsulation twice, it is ensured that the size and position relationship of each several part blank.
Further, the package curing process is：
Removal holding device, by process sequence auxiliary material and pressure equalizing cover plate are placed, and are encapsulated to solidification flat board, enter autoclave
Solidification.
Further, the knockout course is：
Vacuum bag, pressure equalizing cover plate and corresponding auxiliary material are removed, is prized simultaneously using extractor and prize twice mouth position, root
The demoulding is carried out according to mould separating order；After prizing, part is invested on movable core and active block stop, and is departed from fixed core,
Part is separated with movable core, active block stop again.
Further, the machine adds the blanking process to be：
Machine plus blanking are carried out according to part edge line, part surplus is removed, according to heat of the frock material in solidification temperature
The coefficient of expansion carries out blanking with the difference of part thermal coefficient of expansion itself to part edge line.
Further, the quality inspection processes are：
By the way that part is back to into mould inspection and corresponding size detection, spare part outside measurement measurement is qualified, ultrasound
Non-Destructive Testing is qualified, and voidage test passes, presentation quality is good.
The technique for aircraft composite bulkhead structure manufacture of the present invention and method for designing can grind and in-service civil aircraft for China
The development of fuselage composite bulkhead structure provides technical support, reduces construction weight, lifts aeroplane performance, reduces working service
Cost, increases economic efficiency.
Description of the drawings
Accompanying drawing herein is merged in specification and constitutes the part of this specification, shows the enforcement for meeting the present invention
Example, and be used to explain the principle of the present invention together with specification.
Fig. 1 is the fuselage global optimization model of the present invention；
Fig. 2 is the bulkhead structure details FEM model of the present invention；
Fig. 3 is the bulkhead shaping dies schematic diagram of the present invention.
Specific embodiment
To make purpose, technical scheme and the advantage of present invention enforcement clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from start to finish or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than the embodiment of whole.It is exemplary type below with reference to the embodiment of Description of Drawings, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of the work of creation type is not made, belongs to the scope of protection of the invention.Under
Face combines accompanying drawing and embodiments of the invention is described in detail.
In describing the invention, it is to be understood that term " " center ", " longitudinal direction ", " horizontal ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outward " is based on accompanying drawing institute
The orientation for showing or position relationship, are for only for ease of the description present invention and simplify description, rather than indicate or imply the dress of indication
Put or element with specific orientation, with specific azimuth configuration and operation, therefore it is not intended that must be protected to the present invention
The restriction of scope.
First, technique for aircraft composite bulkhead structure design
1st, 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：By airworthiness requirement, the manufacture of civil aircraft parts need to adopt ripe material and
Manufacturing process, and selected material and manufacturing process need to be by approved MAT'L specifications and technological specification ensureing 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：Including rigidity/intensity requirement, fatigue and damage tolerance requirements, the choosing of design margin evaluation
Take and special bearing requirements of airframe structure that seaworthiness specifies；
1.6 weight demands：Require including component weight control and loss of weight；
1.7 cost requirement：Including to design and analysis, in the whole military service cycle for manufacturing, test, use, safeguard and scrapping
Cost control require.
2nd, 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 bulkhead configuration (see accompanying drawing 1)
And it is domestic at present using more ripe prepreg and forming technology, it is determined that using the configuration of the floating frame of shear band+" C " shape, preimpregnation
Material adopts the carbon fibre fabrics of CF3052/BA9916- II, the method that forming technology adopts manual lay+hot pressing can shaping.
3rd, the detailed design of technique for aircraft composite bulkhead structure and analysis
3.1) bulkhead structure design criteria is determined：Edge strip strain in the case where drawing/pressing ultimate load is less than permissible, and in pressure
Edge strip not unstability under contracting ultimate load；Web strain under shearing ultimate load is less than permissible, and does not produce shearing instability；
3.2) structure parameterization modeling, parameter Optimization Analysis are carried out to block mold (see accompanying drawing 2)；
3.3) CONSTRUCTED SPECIFICATION is modeled in detail, checks bulkhead entirety and local load's level, check securing member is connected intensity (see
Accompanying drawing 3)；
3.4) local detail design is adjusted according to analysis result, meets Structural Design Requirement.
2nd, technique for aircraft composite bulkhead structure manufacture
1st, part forming Fixture Design：Including part, solidification flat board, movable core, fixed core, active block stop and pretension
Device；
Core is segmented in the longitudinal direction, and design at per section it is appropriate stick up mouth, be easy to the demoulding.Movable core
Design is the paving and pressurization for the ease of part stile.
Step on fixed core is limited thick step, shoulder height for part thickness lower difference, it act as preventing central authorities
Stile is excessively thin, prevent central stile from can not pressurize, part stile is played a supportive role, and prevention R angles are excessively thin.
Wherein solidify flat board, core, active block stop and pre-tightening apparatus and adopt metal material, metal forming die surface light
Cleanliness is good, and size Control is superior, long perfomance life.The inside C-shaped blank consolidation pressing that holding device can complete paving, then
The R angles filler made using special R angles filler shaping dies is filled to relevant position, outside paving under holding device effect
C-shaped blank.Movable core and active block stop length direction uniformly prize mouth, prizes for mould during the demoulding, and blank paving is to work
At dynamic core flange and active block stop so that part stress is uniform when the demoulding is prized.Most external can increase fibre-reinforced rubber
Compound pressure equalizing cover plate, can uniformly part it is pressurized in autoclave, it is ensured that accessory appearance quality.
2nd, technological process is determined：Including prepare pressure equalizing cover plate, part paving combination, package curing, the demoulding, machine plus blanking and
Quality examination.
Although fuselage bulkhead design of part form is simple, because part curvature is big, auxiliary material can not during cure package
Regular is packaged in piece surface, it is impossible to ensures the surface quality of part, therefore need to manufacture pressure equalizing cover plate.With forming frock as mother
Mould, the process conditions of glass fibre prepreg paving, solidification and part equal thickness from advantage of lower cost, through profile amendment
Afterwards, in process conditions outer surface paving, encapsulation, the enhanced rubber combined pressure equalizing cover plate of cured fiber, 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 it is easy to fill region surface
Projection is produced, therefore the rigidity that 0 ° of fiber fills region is increased when pressure equalizing cover plate makes.
Respectively C-shaped is noted by two groups of inside C-shaped blank consolidation pavings to movable core and fixed core according to laying table
Blank paving at one side surplus goes out crimp, calculates the loading of R angles filler and is made using special R angles filler shaping dies
R angles filler.The movable core of paving part blank is close to fixed core in the presence of holding device, and is adopted in room temperature
It is compacted with vacuum bag encapsulation so that two groups of inside C shape blanks are brought into close contact.R angles filler is positioned over into accurate location, according to paving
Layer angle requirement paving outside C-shaped blank.Crimp at outside C-shaped blank both sides paving, the compacting of vacuum bag encapsulation twice, it is ensured that each
The size and position relationship of part blank.
Removal holding device, by process sequence corresponding auxiliary material and pressure equalizing cover plate are placed, and are encapsulated to solidification flat board, enter heat
Pressure tank solidification.
Vacuum bag, pressure equalizing cover plate and corresponding auxiliary material are removed, is prized simultaneously using extractor and prize twice mouth position, root
The demoulding is carried out according to mould separating order.After prizing, part is invested on movable core and active block stop, and is departed from fixed core,
Part is separated with movable core, active block stop again.
Machine plus blanking are carried out according to part edge line, part surplus is removed.Consider frock material in solidification temperature before blanking
When thermal coefficient of expansion and part thermal coefficient of expansion itself impact of the difference to part edge line.
By the way that part is back to into mould inspection and corresponding size detection, spare part outside measurement measurement is qualified, ultrasound
Non-Destructive Testing is qualified, and voidage test passes, presentation quality is good.
The technique for aircraft composite bulkhead structure design of the present invention and manufacture method can grind and in-service civil aircraft for China
The development of fuselage composite bulkhead structure provides technical support, reduces construction weight, lifts aeroplane performance, reduces working service
Cost, increases economic efficiency.
The above, the only optimum specific embodiment of the present invention, but protection scope of the present invention is not limited thereto,
Any those familiar with the art the invention discloses technical scope in, the change or replacement that can be readily occurred in,
All should be included within the scope of the present invention.Therefore, protection scope of the present invention should be with the protection model of the claim
Enclose and be defined.
Claims (10)
1. a kind of technique for aircraft composite bulkhead structure method for designing, it is characterised in that include
S10：Determine the design requirement of the composite bulkhead
The design requirement includes that overall aircraft layout is wanted with basic parameter, design load, material and technology requirement, working service
Ask, integrity demands, weight demands, cost requirement；
S20：Configuration, material and the process program of technique for aircraft composite bulkhead are determined according to the design requirement
The technique for aircraft composite bulkhead is configured as configuration of the shear band in combination with the floating frame of " C " shape, and prepreg is fine using carbon
Dimensional fabric, forming technology is laid and hot pressing can shaping using manual；
S30：The composite bulkhead modeling and analysis
Determine composite bulkhead structure：The strain in the case where drawing/pressing ultimate load of the edge strip of the composite bulkhead is less than allowable
Strain, and the edge strip not unstability under compression limit load；Web strain under shearing ultimate load is less than permissible, and does not produce
Raw shearing instability；
Composite bulkhead parametric modeling, and model is optimized.
2. technique for aircraft composite bulkhead structure according to claim 1 is designed and manufacture method, it is characterised in that
The total arrangement includes that fuselage cross-section size, fuselage skin and bulkhead piecemeal and segmentation are required with basic parameter；
The design load includes fuselage overall tensile, compression, bending, shearing, torsional load, CAB PRFS load and above-mentioned
The stacking method of several load；
The integrity demands include rigidity/intensity requirement, fatigue and damage tolerance requirements, the selection of design margin evaluation and fit
The special bearing requirements of airframe structure of boat regulation.
3. a kind of technique for aircraft composite bulkhead structure manufacture method, it is characterised in that for mutually tying with " C " shape mansion frame to shear band
The composite bulkhead of conjunction is manufactured, including
Design and produce the frock of the composite bulkhead；The frock includes part, solidification flat board, movable core, fixed core
Mould, active block stop and；
The fixed core is segmented in the longitudinal direction, and is provided with and is stuck up mouth, for the demoulding；Movable core is used for part stile
Paving and pressurization；Fixed core is provided with step, and for limiting thickness, the shoulder height is the lower difference of part thickness；Hold out against dress
Put the inside C-shaped blank consolidation pressing for paving to be completed；
Determine technological process：The technological process includes preparing pressure equalizing cover plate, part paving combination, package curing, the demoulding, machine and adds
Blanking and quality examination.
4. technique for aircraft composite bulkhead structure manufacture method according to claim 3, it is characterised in that the solidification is put down
Plate, core, active block stop and pre-tightening apparatus are made using metal material.
5. technique for aircraft composite bulkhead structure manufacture method according to claim 4, it is characterised in that the preparation is pressed
Cover plate process is：
Pressure equalizing cover plate need to be manufactured according to piece surface flatness requirement after part curvature and encapsulation；With forming frock as master mold, adopt
With glass fibre prepreg paving, solidification and the process conditions of part equal thickness, after profile amendment, spread in process conditions outer surface
Patch, encapsulation, the enhanced rubber combined pressure equalizing cover plate of cured fiber, for the guarantee in part outer surface type face.
6. technique for aircraft composite bulkhead structure manufacture method according to claim 5, it is characterised in that the part paving
Anabolic process is：
Respectively according to laying table by two groups of inside C-shaped blank consolidation pavings to movable core and fixed core, C-shaped blank is in list
Paving at the surplus of face goes out crimp, calculates the loading of R angles filler and makes R angles filler using special R angles filler shaping dies,
The movable core of paving part blank is close to fixed core with holding device, and in room temperature using vacuum bag encapsulation pressure
It is real so that two groups of inside C-shaped blanks are brought into close contact, according to laying angle requirement paving outside C-shaped blank, outside C-shaped blank two
Crimp at the paving of side, the compacting of vacuum bag encapsulation twice, it is ensured that the size and position relationship of each several part blank.
7. technique for aircraft composite bulkhead structure manufacture method according to claim 6, it is characterised in that the package curing
Process is：
Removal holding device, by process sequence auxiliary material and pressure equalizing cover plate are placed, and are encapsulated to solidification flat board, are entered autoclave and are consolidated
Change.
8. technique for aircraft composite bulkhead structure manufacture method according to claim 7, it is characterised in that the knockout course
For：
Vacuum bag, pressure equalizing cover plate and corresponding auxiliary material are removed, is prized simultaneously using extractor and prize twice mouth position, according to mould
Tool disengaging order carries out the demoulding；After prizing, part is invested on movable core and active block stop, and is departed from fixed core, then will
Part is separated with movable core, active block stop.
9. technique for aircraft composite bulkhead structure manufacture method according to claim 8, it is characterised in that the machine adds blanking
Process is：
Machine plus blanking are carried out according to part edge line, part surplus is removed, according to thermal expansion of the frock material in solidification temperature
Coefficient carries out blanking with the difference of part thermal coefficient of expansion itself to part edge line.
10. technique for aircraft composite bulkhead structure manufacture method according to claim 9, it is characterised in that the quality inspection
The process of looking into is：
By the way that part is back to into mould inspection and corresponding size detection, spare part outside measurement measures qualified, ultrasonic non-destructive
Detection is qualified, and voidage test passes, presentation quality is good.
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| CN107839254A (en) * | 2017-11-21 | 2018-03-27 | 江苏美龙航空部件有限公司 | A kind of preparation method and mould of glass fibre bend pipe |
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| CN112810182A (en) * | 2020-12-29 | 2021-05-18 | 江苏新扬新材料股份有限公司 | Forming method of composite material cylindrical support |
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