CN102582091B - A kind of airframe sphere frame and manufacture method thereof - Google Patents
A kind of airframe sphere frame and manufacture method thereof Download PDFInfo
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- CN102582091B CN102582091B CN201210001575.6A CN201210001575A CN102582091B CN 102582091 B CN102582091 B CN 102582091B CN 201210001575 A CN201210001575 A CN 201210001575A CN 102582091 B CN102582091 B CN 102582091B
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Abstract
The invention provides a kind of manufacture method of airframe sphere frame, comprise step: require to obtain covering curved surface according to airplane design; Described covering curved surface is divided into multiple These strip-shaped sections, and by equal-area method, described These strip-shaped sections is launched into plane; Determine the breach Δ t=Rcos α (tg π/n-π/n) between the theoretical boundary of described These strip-shaped sections and actual boundary, wherein R is the radius of covering curved surface place spheroid, α is the angle of gap position and spheroid meridian plane, and n is the number of the These strip-shaped sections that described spheroid divides; Cutting one-way tape prepreg material is carried out according to the size of the shape cooperation breach of the expansion plane of described These strip-shaped sections; By the one-way tape prepreg material paving after cutting on sphere frame mould; Carry out solidification of hot-press tank shaping; Carry out supplementary machining.The present invention also provides a kind of airframe sphere frame, and it adopts said method to make.Airframe sphere frame of the present invention can meet the requirement of lighting, high strength.
Description
Technical field
The present invention relates to a kind of airframe sphere frame and manufacture method thereof, particularly relate to airframe sphere frame and the manufacture method thereof of the paving of a kind of one-way tape prepreg material.
Background technology
Composite obtains with the performance of its uniqueness and applies more and more widely in aerospace structure.Advanced composite material is applied to aircraft main force support structure, improve the consumption of advanced composite material on aircaft configuration, now become the important indicator weighing aircaft configuration advance, reduce one of aircraft development cost, the important means improving aeroplane performance and the market competitiveness especially.
Sphere frame is the back-end box of airframe, mainly bears airtight pressure effect.Tradition sphere frame is metal riveting structure, and rapport is complicated, and efficiency of assembling is low.Composite sphere mount structure have lightweight, manufacture that assembling is simple, durability high.
Current aircraft of new generation all uses composite sphere mount structure, wherein the material of A380 sphere frame is carbon fiber epoxy based composites panel and PMI foam sandwich, make use of resin molding infiltration be shaped (RFI) technique and autoclave technique regelate shaping, B787 sphere frame uses medium modulus carbon fiber and foam, utilizes vacuum aided liquid molding process VARTM (Vacuum-Assited Resin Transfer Molding) shaping.
Most existing sphere mount structure selects carbon fiber corrugationless fabric as main material, by liquid molding process (RFI and VARTM) by resin injection in dry state fabric, its advantage be manufacture simple and convenient.But also can be good just because of its fibre deformation type, cause its machine direction off-design angle, and liquid formed product porosity is large, fiber volume fraction is low, larger safety coefficient need be adopted to go design, cause weight larger.
Summary of the invention
In order to solve above-mentioned purpose, the invention provides a kind of method for designing of airframe sphere frame, meeting the requirement of lighting, high strength.
In order to solve the problem, according to the manufacture method of airframe sphere frame of the present invention, comprise step:
(1). require according to airplane design the covering curved surface obtaining sphere frame;
(2). described covering curved surface is divided into multiple These strip-shaped sections, and by equal-area method, described These strip-shaped sections is launched into plane;
(3). determine the breach Δ t=Rcos α (tg π/n-π/n) between the theoretical boundary of described These strip-shaped sections and actual boundary, wherein R is the radius of covering curved surface place spheroid, α is the angle of gap position and spheroid meridian plane, and n is the number of the These strip-shaped sections that described spheroid divides;
(4). carry out cutting one-way tape prepreg material according to the size of the shape cooperation breach of the expansion plane of described These strip-shaped sections;
(5). by the one-way tape prepreg material paving after cutting on sphere frame mould;
(6). it is shaping to carry out solidification of hot-press tank;
(7). supplementary machining is carried out to the sphere frame after shaping.
Wherein, in step (2), by FiberSIM software, described These strip-shaped sections is launched into plane.
Wherein, during one-way tape prepreg material after paving cutting, on sphere frame mould, the position line of every sheet one-way tape prepreg material is projected by laser, every sheet one-way tape prepreg material is positioned, during paving, ensures that the datum line of every sheet one-way tape prepreg material overlaps with position line.
Wherein, during one-way tape prepreg material after paving cutting, number of stories m is determined according to the thickness requirement of sphere frame and the thickness of individual layer one-way tape prepreg material, angled staggered paving between each layer.
Preferably, the angle between the second layer and ground floor is 2 π/m, and the angle between the relatively last even level of a rear even level is 2 π/m, and the angle between the relatively last odd-level of a rear odd-level is-2 π/m.
Preferably, the angle between the second layer and ground floor is-2 π/m, and the angle between the relatively last even level of a rear even level is-2 π/m, and the angle between the relatively last odd-level of a rear odd-level is 2 π/m.
Wherein, described one-way tape prepreg material adopts carbon fiber one-way band prepreg.
The present invention also provides a kind of airframe sphere frame, and it adopts above-mentioned manufacture method to make.
Beneficial effect of the present invention:
The present invention adopts carbon fiber one-way band prepreg to be main material, and by manual paving, solidification of hot-press tank, designs and can bear high strength pressure, the sphere mount structure of large scale (maximum cross-section more than diameter 3m) lightweight.
The present invention, also under the condition not having automation laying apparatus (automated tape-laying machine, automatic fiber placement machine), is aided with general positioning means by accurate cut-parts design and ensure that structure laying angle, solve the precision manufactureing problem of large scale curved-surface structure.
Accompanying drawing explanation
Fig. 1 is the flow chart of the manufacture method according to airframe sphere frame of the present invention;
Fig. 2 is the schematic diagram of covering curved surface;
Fig. 3 is the schematic diagram that breach is formed;
Fig. 4 is the schematic diagram of paving covering curved surface cut-parts;
Fig. 5 is the schematic diagram of paving 2 layers of covering curved surface cut-parts.
Detailed description of the invention
As shown in Figure 1, it illustrates the flow chart of the manufacture method of airframe sphere frame of the present invention, the method comprising the steps of:
(1). require according to airplane design the covering curved surface obtaining sphere frame;
(2). described covering curved surface is divided into multiple These strip-shaped sections, and by equal-area method, described These strip-shaped sections is launched into plane; Preferably, Fibersim composite Materials Design software is utilized to launch described These strip-shaped sections;
(3). determine the breach Δ t=Rcos α (tg π/n-π/n) between the theoretical boundary of described These strip-shaped sections and actual boundary, wherein R is the radius of covering curved surface place spheroid, α is the angle of gap position and spheroid meridian plane, and n is the number of the These strip-shaped sections that described spheroid divides;
(4). carry out cutting one-way tape prepreg material according to the size of the shape cooperation breach of the expansion plane of described These strip-shaped sections;
(5). by the one-way tape prepreg material paving after cutting on sphere frame mould;
(6). it is shaping to carry out solidification of hot-press tank;
(7). supplementary machining is carried out to the sphere frame after shaping.
Principle of the present invention is: in design-manufacture process, needs covering Doubly curved surfaces to become plane, for prepreg cutting, then also needs the planar materials paving after by cutting to become curved-surface structure, experience development of a sphere plane, the process of plane paving curved surface.Because sphere to open up sphere, any expansion plane is all a kind of approximate expansion.The expansion of curved surface has multiple method, current engineering is substantially launch according to homalographic method, and it is petal that this structure adopts warp sphere to be divided into some strips, as shown in Figure 2.By equal-area method by petal for strip generate plane.Under this methodology, the area launching plane is equal with area of spherical surface.In plane paving curved surface process, each launches plane only radially can do bend in one direction, can not be reduced to former curved surface, therefore can not be reduced to complete sphere during the plane paving launched by equal-area method completely, can be jagged.
Fig. 3 is the schematic diagram of breach, represent the situation of paving when whole spheroid being cut to 4 pieces, because every plate plane cut-parts all only can bend in one direction, can not bend by conformal, therefore plane is being reduced in curved surface process, show as the curved surface after plain bending and can not cover former curved surface completely, there is between the theoretical boundary L of each cut-parts and actual boundary L ' breach Δ t.
Pass through the derivation of equation:
Breach Δ t=Rcos α (tg π/n-π/n), wherein R is sphere frame place radius of sphericity, and α is the angle of gap position and spheroid meridian plane, and n is the number that spheroid divides cut-parts.
By optimizing n value to make Δ t at OK range, according to breach size, expansion plane is revised simultaneously, and coordinate suitable cut-parts overlap joint, to reach the object that paving goes out complete corrugationless sphere.
After determining individual layer Doubly curved surfaces mode, according to thickness requirement and the individual layer prepreg material thickness of structure, determine number of stories m, then by the angled paving completing remainder layer between every layer, more firm structure can be obtained like this.
In accurate cut-parts design basis, by automatic blanking machine, cutting is carried out to prepreg, to ensure cutting precision, when paving, accurately need locate each cut-parts, laser positioning means can be selected, mould is accurately launched the position line of every sheet cut-parts, datum line during paving in guarantee cut-parts and the relation of position line, to make paving meet designing requirement, improve paving quality.
After paving completes, structure is encapsulated, enter solidification of hot-press tank, form final products.
The following detailed description of a specific embodiment of the present invention:
Obtain (establishing curved surface place radius of sphericity 2200mm) after covering curved surface, according to one-way tape width (being assumed to be 300mm) and curved surface meridian girth, determine minimumly sphere to be divided into 11 pieces, the n value of the spheroid of corresponding covering curved surface is 49.According to breach Δ t=Rcos α (tg л/n-л/n), maximum breach Δ t is 0.198mm (α=0, on meridian plane).Because notch size is very little, so revise the plane launched by homalographic according to the size of breach maximum on meridian plane, make its width increase 0.2mm, carry out one-way tape cutting by revised expanded view.
After determining individual layer Doubly curved surfaces mode, according to thickness requirement and the individual layer prepreg material thickness of structure, determine number of stories m, to select CYCOM977-2-35%-12KHTS-134-300 material, single layer of material thickness is 0.131mm, and topology requirement thickness is 2mm, then need 16 layers of laying.Determine that the interlayer anglec of rotation is 22.5 degree according to every layer of angle 2 π/m, determine that between each laying, angle is 0/ ± 22.5/ ± 45/ ± 67.5/90.Such as, ground floor is 0 degree, and the second layer is+22.5, and third layer is-22.5, by that analogy.Certainly, being staggered into except angle setting except this, can also be that each layer is along staggering clockwise or along angled counterclockwise.
Fig. 5 shows the schematic diagram of 2 layers of laying, and the second layer is the result after ground floor rotates 22.5 degree.
After paving completes, structure is encapsulated, enter solidification of hot-press tank.
After going out tank, excision covering periphery process allowance, processes system architecture opening, forms final products.
The present invention is with carbon fiber one-way band prepreg for main material, and by manual paving, solidification of hot-press tank, designs and can bear high strength pressure, the structure of large scale (maximum cross-section more than diameter 3m) lightweight.The method, also under the condition not having automation laying apparatus (automated tape-laying machine, automatic fiber placement machine), is aided with general positioning means by accurate cut-parts design and ensure that structure laying angle, solve the precision manufactureing problem of large scale curved-surface structure.
Described in the present invention, concrete case study on implementation is only better case study on implementation of the present invention, is not used for limiting practical range of the present invention.Namely all equivalences done according to the content of the present patent application the scope of the claims change and modify, and all belong to protection scope of the present invention.
Claims (8)
1. a manufacture method for airframe sphere frame, is characterized in that, comprises step:
(1). require according to airplane design the covering curved surface obtaining sphere frame;
(2). described covering curved surface is divided into multiple These strip-shaped sections, and by equal-area method, described These strip-shaped sections is launched into plane;
(3). determine the breach Δ t=Rcos α (tg π/n-π/n) between the theoretical boundary of described These strip-shaped sections and actual boundary, wherein R is the radius of covering curved surface place spheroid, α is the angle of gap position and spheroid meridian plane, and n is the number of the These strip-shaped sections that described spheroid divides;
(4). carry out cutting one-way tape prepreg material according to the size of the shape cooperation breach of the expansion plane of described These strip-shaped sections, wherein according to the size of breach maximum on meridian plane, the plane launched by homalographic is revised, carry out one-way tape cutting by revised expanded view;
(5). by the one-way tape prepreg material paving after cutting on sphere frame mould, angled staggered paving between each layer;
(6). it is shaping to carry out solidification of hot-press tank;
(7). supplementary machining is carried out to the sphere frame after shaping.
2. manufacture method according to claim 1, is characterized in that, in step (2), by FiberSIM software, described These strip-shaped sections is launched into plane.
3. manufacture method according to claim 1 and 2, it is characterized in that, during one-way tape prepreg material after paving cutting, the position line being projected every sheet one-way tape prepreg material by laser on sphere frame mould is positioned every sheet one-way tape prepreg material.
4. manufacture method according to claim 1 and 2, is characterized in that, during one-way tape prepreg material after paving cutting, determines number of stories m according to the thickness requirement of sphere frame and the thickness of individual layer one-way tape prepreg material.
5. manufacture method according to claim 4, is characterized in that, the angle between the second layer and ground floor is 2 π/m, and the angle between the relatively last even level of a rear even level is 2 π/m, and the angle between the relatively last odd-level of a rear odd-level is-2 π/m.
6. manufacture method according to claim 4, it is characterized in that, angle between the second layer and ground floor is-2 π/m, and the angle between the relatively last even level of a rear even level is-2 π/m, and the angle between the relatively last odd-level of a rear odd-level is 2 π/m.
7. manufacture method according to claim 1 and 2, is characterized in that, described one-way tape prepreg material adopts carbon fiber one-way band prepreg.
8. an airframe sphere frame, it adopts the manufacture method according to any one of claim 1 to 7 to make.
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| CN201210001575.6A CN102582091B (en) | 2012-01-05 | 2012-01-05 | A kind of airframe sphere frame and manufacture method thereof |
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| CN201210001575.6A CN102582091B (en) | 2012-01-05 | 2012-01-05 | A kind of airframe sphere frame and manufacture method thereof |
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| CN102582091B true CN102582091B (en) | 2015-09-30 |
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| US9844904B2 (en) * | 2014-02-18 | 2017-12-19 | The Boeing Company | Formation of thermoplastic parts |
| CN105467950A (en) * | 2015-10-12 | 2016-04-06 | 无锡清杨机械制造有限公司 | Design method of composite material shaping die |
| CN106346800B (en) * | 2016-09-30 | 2019-05-10 | 咸宁海威复合材料制品有限公司 | A kind of preparation method of propeller blade |
| CN107045561A (en) * | 2016-12-26 | 2017-08-15 | 中国航空工业集团公司西安飞机设计研究所 | A kind of metal ball surface frame and its design method |
| CN108973160B (en) * | 2017-06-05 | 2021-10-12 | 中国商用飞机有限责任公司 | Prepreg positioning method for performing composite material thermal diaphragm |
| CN108052710A (en) * | 2017-11-29 | 2018-05-18 | 中国航空工业集团公司西安飞机设计研究所 | A kind of technique for aircraft composite spherical surface mount structure design method |
| CN111605225A (en) * | 2020-03-25 | 2020-09-01 | 海鹰空天材料研究院(苏州)有限责任公司 | Co-bonding curing molding method for large-curvature spherical frame of airplane |
| CN111469441B (en) * | 2020-04-22 | 2021-10-22 | 常州市新创智能科技有限公司 | Guide plate layering process |
| CN112590250A (en) * | 2020-12-12 | 2021-04-02 | 江西洪都航空工业集团有限责任公司 | Method for manufacturing low-curvature parts in batches by adopting automatic tape laying technology |
| CN114074435A (en) * | 2021-03-26 | 2022-02-22 | 亨弗劳恩(江苏)复合材料研发有限公司 | Preparation method of thermoplastic composite material sheet |
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| DE102007003275B4 (en) * | 2007-01-23 | 2013-11-28 | Airbus Operations Gmbh | Shell element as part of an aircraft fuselage |
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| DE102007003277A1 (en) * | 2007-01-23 | 2008-07-24 | Airbus Deutschland Gmbh | Hull of an aircraft or spacecraft in CFRP metal. Hybrid construction with a metal frame |
| CN101219587A (en) * | 2007-12-28 | 2008-07-16 | 同济大学 | Composite stressed-skin construction for fuselage and technique of preparing the same |
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