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 PDF

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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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core model
paving
technique
bulkhead
aircraft
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CN106626434A (en
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王瑜
胡海阳
王振世
刘利阳
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Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
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Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29CSHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28Shaping operations therefor
    • B29C70/30Shaping 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
    • B29C70/34Shaping 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
    • B29C70/342Shaping 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
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29CSHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28Shaping operations therefor
    • B29C70/54Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29LINDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00Other particular articles
    • B29L2031/30Vehicles, e.g. ships or aircraft, or body parts thereof
    • B29L2031/3076Aircrafts

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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

A kind of manufacture of technique for aircraft composite bulkhead structure and design method
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.
CN201611177437.8A 2016-11-29 2016-12-19 A kind of manufacture of technique for aircraft composite bulkhead structure and design method Active CN106626434B (en)

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* Cited by examiner, † Cited by third party
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CN107839254B (en) * 2017-11-21 2024-06-07 江苏美龙航空部件有限公司 Preparation method and mold for glass fiber bent pipe
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CN112810182B (en) * 2020-12-29 2021-11-30 江苏新扬新材料股份有限公司 Forming method of composite material cylindrical support
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CN115071163B (en) * 2022-06-22 2024-03-08 沈阳飞机工业(集团)有限公司 Integral co-curing forming process for S-shaped air inlet channel of multi-bulkhead carbon fiber composite material
CN115071175B (en) * 2022-06-22 2024-01-23 沈阳飞机工业(集团)有限公司 Forming tool for multiple high-size composite material bulkhead outside large cylinder section

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102982200A (en) * 2012-11-06 2013-03-20 西北工业大学 Design method of airplane frame and rib type sheet metal part processing model
CN103310032A (en) * 2012-12-25 2013-09-18 中国航空工业集团公司沈阳飞机设计研究所 Aircraft structure design method based on parametric component
CN103496180A (en) * 2013-09-18 2014-01-08 沈阳飞机工业(集团)有限公司 Composite material E-shaped frame forming mould and forming method thereof
CN103950552A (en) * 2014-04-25 2014-07-30 浙江大学 Digitized correcting method for assembly deformation of aircraft panels based on six-shaft numerical control positioner
CN105005671A (en) * 2015-07-30 2015-10-28 中航沈飞民用飞机有限责任公司 Dynamics simulation analysis method of uniformly distributed load bearing system
CN105528481A (en) * 2015-12-02 2016-04-27 中国商用飞机有限责任公司北京民用飞机技术研究中心 Optimization method and apparatus of airplane wing structure
CN106156403A (en) * 2016-06-21 2016-11-23 南京航空航天大学 Based on the hypersonic aircraft spar structure analysis method for reliability that Stress strength interference is theoretical

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2984845B1 (en) * 2011-12-21 2014-07-11 Airbus Operations Sas ANTI-SPEED AIRCRAFT FUSELAGE STRUCTURE ELEMENT
ES2662853T3 (en) * 2014-12-29 2018-04-10 Airbus Operations S.L. Tail cone of an aircraft

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102982200A (en) * 2012-11-06 2013-03-20 西北工业大学 Design method of airplane frame and rib type sheet metal part processing model
CN103310032A (en) * 2012-12-25 2013-09-18 中国航空工业集团公司沈阳飞机设计研究所 Aircraft structure design method based on parametric component
CN103496180A (en) * 2013-09-18 2014-01-08 沈阳飞机工业(集团)有限公司 Composite material E-shaped frame forming mould and forming method thereof
CN103950552A (en) * 2014-04-25 2014-07-30 浙江大学 Digitized correcting method for assembly deformation of aircraft panels based on six-shaft numerical control positioner
CN105005671A (en) * 2015-07-30 2015-10-28 中航沈飞民用飞机有限责任公司 Dynamics simulation analysis method of uniformly distributed load bearing system
CN105528481A (en) * 2015-12-02 2016-04-27 中国商用飞机有限责任公司北京民用飞机技术研究中心 Optimization method and apparatus of airplane wing structure
CN106156403A (en) * 2016-06-21 2016-11-23 南京航空航天大学 Based on the hypersonic aircraft spar structure analysis method for reliability that Stress strength interference is theoretical

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
基于MSC.Nastran/HyperWorks的薄壁圆筒隔;李宇峰;《强度与环境》;20150815;35-39页
波音737-CL飞机客舱隔框改装或修理常见偏离的研究;杨延波;《山东工业技术》;20140915;187-188页

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