CN111470068B - Grille cover body structure for aircraft and manufacturing method thereof - Google Patents
Grille cover body structure for aircraft and manufacturing method thereof Download PDFInfo
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- CN111470068B CN111470068B CN202010191075.8A CN202010191075A CN111470068B CN 111470068 B CN111470068 B CN 111470068B CN 202010191075 A CN202010191075 A CN 202010191075A CN 111470068 B CN111470068 B CN 111470068B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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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
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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
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
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- Astronomy & Astrophysics (AREA)
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- Aviation & Aerospace Engineering (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention discloses a grille cover body structure used on an aircraft and a preparation method thereof, wherein the grille cover body structure comprises: an inner skin; an outer skin; and a plurality of longitudinal bars positioned between the inner skin and the outer skin; the grille cover body structure further comprises; the box-shaped parts are positioned in a groove formed by adjacent longitudinal ribs and an inner skin, and the box-shaped parts are adjacent to each other to form a plurality of transverse ribs perpendicular to the longitudinal ribs. The technical scheme of the invention adopts the technical scheme that the grid cover body is composed of an inner covering, a grid interlayer and an outer covering, so that the light weight and high rigidity of the grid cover body structure are taken into consideration, and the grid cover body has higher structural performance; the technical scheme of the invention adopts a co-curing molding process method to realize the integrated manufacture of the grille cover body structure.
Description
Technical Field
The invention relates to the field of aircraft grille cover body structures. And more particularly, to a grille cover structure for use on an aircraft and a method of making the same.
Background
The advanced composite material has the advantages of high specific strength, large specific stiffness, good damping characteristic, long fatigue life, designable structure and the like, and is widely applied to the fields of aviation, aerospace, machinery, biology, medicine, sports and the like in recent years. The adoption of a reinforcement structure form is one of effective forms for improving the bearing capacity and rigidity of the laminated plate, wherein the grille cover body structure is taken as a special reinforcement structure, and the grid cover body structure draws more and more attention in the composite material world at home and abroad with stronger designability and various excellent performances, and is determined as one of three candidate manufacturing technologies (a reinforcement structure, a sandwich structure and a grille cover body structure) of the next generation of return type aerospace vehicle shell.
However, the grating cover body structure prepared by the technology has the advantages that under the action of impact load, cracks are easy to propagate, and the impact resistance is poor; the grid cover body structure of the aluminum alloy material has poor corrosion resistance; and the grille cover body structure is difficult to manufacture integrally. Therefore, there is a need to provide a new grille cover structure for an aircraft and a method of making the same.
Disclosure of Invention
It is an object of the present invention to provide a grille cover structure for use on an aircraft.
It is another object of the present invention to provide a method of making a grille cover structure for use on an aircraft.
In order to achieve the purpose, the invention adopts the following technical scheme:
in a first aspect, the present invention provides a grille cover structure for use on an aircraft, the grille cover structure comprising:
an inner skin;
an outer skin; and
a plurality of longitudinal bars positioned between the inner skin and the outer skin;
the grille cover structure further includes:
a plurality of box-shaped elements located in the grooves formed by the adjacent longitudinal bars and the inner skin, an
And a plurality of transverse ribs which are vertical to the longitudinal ribs are formed between the adjacent box-shaped parts.
Optionally, the box comprises a water-soluble core in a hexahedral structure; and
the prepreg layer is coated on the five surface bodies of the water-soluble mold core;
wherein the surface of the box-shaped piece contacting with the inner skin is not paved.
Optionally, the longitudinal bars are semi-cured and formed on the inner skin in a pre-forming process,
the box-shaped pieces are sequentially laid in grooves formed by adjacent longitudinal ribs and the inner skin;
and transverse ribs are formed between adjacent box-shaped parts by prepreg paving layers.
Optionally, the outer skin is coated on the longitudinal bars, the transverse bars and the box-shaped member by a RTM process.
Optionally, preparing a water-soluble core of the box part by using a water-soluble core forming die of the box part;
laying up prepreg on the surfaces of the five surfaces of the water-soluble mold core by a laying-up process to form a box-shaped part; wherein the surface of the box-shaped piece in contact with the inner skin is not paved;
vacuum bagging to cure the box;
placing the box-shaped piece in the groove and co-curing and molding the box-shaped piece and the transverse rib;
perforating the outer side surface opposite to the unpaved surface of the box-shaped part, and injecting a core solvent into the box-shaped part to form a hollow prepreg box-shaped part;
and filling the open holes of the box-shaped part by using a prepreg patch process to form a closed box-shaped part.
Optionally, the outer skin is a fabric preform.
Optionally, the material of the longitudinal bars, the transverse bars and the inner skin is one or more of a fiber reinforced material and a resin matrix material.
Optionally, the prepreg is formed from the fibrous reinforcement material and the resin matrix material.
In a second aspect, the present invention provides a method of making a grille mask body structure according to any one of the first aspects, comprising:
semi-curing the plurality of longitudinal bars by a pre-forming curing process to form the inner skin;
sequentially laying a plurality of box-shaped pieces in a groove formed by adjacent longitudinal ribs and the inner skin;
forming transverse ribs between adjacent connected box-shaped parts by using prepreg paving layers;
and coating the outer skin on the longitudinal ribs, the transverse ribs and the box-shaped piece.
The invention has the following beneficial effects:
the technical scheme of the invention adopts the technical scheme that the grid cover body is composed of an inner covering, a grid interlayer and an outer covering, so that the light weight and high rigidity of the grid cover body structure are taken into consideration, and the grid cover body has higher structural performance; the technical scheme of the invention adopts a co-curing molding process method to realize the integrated manufacture of the grille cover body structure.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 illustrates a schematic view of a grille cover construction provided by an embodiment of the present invention;
fig. 2 shows another schematic diagram of a grille cover structure provided by an embodiment of the invention:
FIG. 3 illustrates a schematic view of a structural lay-up of a grille cover provided by an embodiment of the present invention;
reference numerals: an inner skin 1; an outer skin 2; a longitudinal rib 3; a box-shaped member 4; and a transverse rib 5.
Detailed Description
In order to more clearly illustrate the invention, the invention is further described below with reference to preferred embodiments and the accompanying drawings. Similar parts in the figures are denoted by the same reference numerals. It is to be understood by persons skilled in the art that the following detailed description is illustrative and not restrictive, and is not to be taken as limiting the scope of the invention.
As shown in fig. 1 and 2, a first embodiment of the present invention discloses a grille cover structure for an aircraft, the grille cover structure including:
an inner skin 1;
an outer skin 2; and
a plurality of longitudinal bars 3 positioned between the inner skin 1 and the outer skin 2;
the grille cover structure further includes:
a plurality of box-shaped elements 4 located in the recesses formed by adjacent longitudinal ribs 3 and the inner skin 1, and
and a plurality of transverse ribs 5 which are vertical to the longitudinal ribs 3 are formed between the adjacent box-shaped parts 4.
The technical scheme of the invention adopts the technical scheme that the grid cover body is composed of an inner covering, a grid interlayer and an outer covering, so that the light weight and high rigidity of the grid cover body structure are taken into consideration, and the grid cover body has higher structural performance; the technical scheme of the invention adopts a co-curing molding process method to realize the integrated manufacture of the grille cover body structure. Compared with a composite material honeycomb sandwich structure with the same weight, the structure can achieve the remarkable effect that the bending rigidity of the whole cover body is improved by more than 30%.
Compared with the traditional wallboard structure, the sandwich structure of the grille cover body structure disclosed by the embodiment of the invention is relatively independent, cracks are not easy to propagate under the action of impact load, and the impact resistance is good. Compared with the aluminum alloy grating cover body structure, the grating cover body structure provided by the embodiment of the invention further improves the specific strength and specific modulus of the structure, overcomes the corrosion resistance of the structure, and increases the flexibility of structural design and manufacturing.
In some optional implementations of the present embodiment, as shown in fig. 3, the longitudinal ribs 3 are semi-cured in a pre-forming process formed on the inner skin 1,
the box-shaped pieces 4 are sequentially laid in the grooves formed by the skins in the adjacent longitudinal ribs 3;
the transverse ribs 5 are formed between the adjacent box-shaped parts 4 by prepreg paving.
In a specific example, as shown in fig. 3, the inner skin 1 and the longitudinal ribs 3 form a groove for accommodating the box in a co-curing process to lay the box 4, the box 4 is laid sequentially along the extending direction, and two adjacent box 4 are connected by the transverse ribs to form a strip. In a specific example, a cavity for accommodating the longitudinal ribs 3 can be formed on the inner skin in a left-right C-shaped layering mode, so that the longitudinal ribs 3 can be positioned during the curing process of the inner skin 1 and the longitudinal ribs 3, and the rigidity of the whole grille cover body structure can be effectively improved.
In some optional realizations of the present embodiment, the box-shaped element 4 comprises a water-soluble core in hexahedral configuration; and
the prepreg layer is coated on the five surface bodies of the water-soluble mold core;
wherein the surface of the box-shaped element 4 in contact with the inner skin 1 is not laid.
As shown in fig. 3, the placement position of the box 4 is the basis for laying the transverse rib prepreg, and in one specific example, a water-soluble core is used to mold the box. The water-soluble core is of a hexahedral structure, and the characteristic that the soluble or meltable core mold is well soluble or meltable under certain physical conditions is utilized to prepare the grating interlayer in the grating cover body structure, so that the integral forming tool of the grating cover body structure can be effectively realized.
In some optional implementations of this embodiment, the water-soluble core of the box is prepared using a water-soluble core forming mold of the box;
laying a prepreg on the surfaces of five surfaces of the water-soluble mold core by a laying process to form a box-shaped part; wherein the surface of the box-shaped piece in contact with the inner skin is not paved;
vacuum bag pressing and curing the initial box-shaped piece;
placing the box-shaped piece in the groove and co-curing and molding the box-shaped piece and the transverse rib;
perforating the outer side surface opposite to the unpaved surface of the box-shaped part, and injecting a core solvent into the box-shaped part to form a hollow prepreg box-shaped part;
and filling the open holes of the box-shaped part by using a prepreg patch process to form a closed box-shaped part.
In one specific example, the water soluble core of the box is first prepared with the water soluble core forming mold of the box and then the box is laid down on five face surfaces of the water soluble core in a 4-ply quasi-isotropic unidirectional prepreg, i.e. a lay-up of [0/45/90/-45] parameters of 0.5 mm. Since the box presents a surface for co-curing the integral molding in contact with the inner skin, the surface of the box in contact with the inner skin is not layered. And then, the initial box-shaped part is pressed and solidified by a vacuum bag, and the pressed and solidified box-shaped part is further placed in a groove formed by the inner skin and the longitudinal ribs and is co-solidified and molded with the transverse ribs. Further, the outside surfaces of the co-cured molded box opposite the non-laid side are perforated and a core solvent is injected into the box to form a hollow prepreg box. Because the water-soluble core in the box-shaped part has good water solubility and solubility, after the core solvent is injected, the core is dissolved in the box-shaped part and becomes a vacuum state, and finally, the opening of the box-shaped part is filled by utilizing a prepreg patch process to form a closed box-shaped part. In conclusion, the integrated grid cover body structure of the transverse ribs, the longitudinal ribs, the inner skin and the box-shaped parts is formed with a plurality of independent grids, so that the rigidity of the structure is effectively improved, and the quality of the structure is greatly reduced due to the box-shaped parts with hollow interiors.
In some optional implementations of this embodiment, the outer skin is a fabric preform.
In some optional implementations of this embodiment, the material of the longitudinal ribs, the transverse ribs, and the inner skin is one or more of a fiber reinforced material and a resin matrix material.
In some optional implementations of this embodiment, the prepreg is formed from the fibrous reinforcement material and the resin matrix material.
In one specific example, the fiber reinforced material may be ZT8E carbon fiber and its fabric available from Zhongzi technology, Inc. The properties of the domestic ZT 8E/bismaleimide composite material unidirectional plate can be seen in Table 1. As shown in the table, according to early characterization tests, ZT8E has good interface matching property with most of brands of epoxy resin, bismaleimide resin and cyanate resin for composite materials, and carbon fiber prepreg with excellent laying performance can be prepared.
TABLE 1 mechanical properties of domestic ZT8E/SQ6419A bismaleimide resin composite material unidirectional plate
In another specific example, according to the temperature characteristics of the carbon fiber composite material, the resin matrix material can be used for molding the cabin section by adopting two forms of bismaleimide resin systems, such as the curing process parameters and the molding parts of the bismaleimide resins shown in table 2, SQ6419A belongs to the bismaleimide resin for preparing the prepreg, SQ6420 belongs to the modified low-viscosity bismaleimide resin for RTM, the two resins can realize good co-curing, the interface performance is good, and the inspection of model products is obtained.
| Resin brand | Type of resin | Curing temperature | Molded part |
| SQ6419A resin | Modified double horse | 180℃2h/200℃6h | Ribs, end frames |
| SQ6420 resin | Modified RTM double horse | 180℃2h/200℃6h | Covering skin |
TABLE 2 resin List for composite Molding
In some optional implementations of this embodiment, the outer skin is coated on the longitudinal bars, the transverse bars, and the box-shaped member in an RTM process. The RTM forming process has strong adaptability to the geometric structure, can ensure high precision on both sides, and can realize one-time integral manufacture of structures with complex shapes, thereby solving the technical problem in the field of composite material manufacture.
The RTM injection process is adopted for the outer skin of the large-size composite material, a relatively simple skin structure is beneficial to forming a relatively simple flow channel, and after resin is injected into the outer skin, due to the fact that the resin has good fluidity, good skin forming quality and double-sided high precision of the structure can be achieved at the same time, and the purpose of high-reliability integral manufacturing of the complex cover body composite material structure is achieved.
In one specific example, a strip is wrapped by way of a cap-type over-wrap ply, and the wrapped strip is pre-cured. If further weight reduction is needed, under the condition that the design rigidity permits, the strip-shaped part can be coated by a hat-shaped upper wrapping mode to form an integral strip-shaped part, and finally the sandwich structure of the grating is spliced, so that the thickness of the lower bottom surface is reduced by the aid of the layering mode, and the weight of the grating cover body structure is further reduced.
Those skilled in the art can combine various layering modes of different external skins, internal skins and box-shaped parts, longitudinal ribs and transverse ribs according to the performance requirements of different grille cover body structures.
The grille cover body structure of the embodiment of the invention has the following characteristics: 1) the geometric adaptability is strong. Because the resin systems with different rheological properties are respectively adopted in the molding process, the fluidity of the resin system can be selected according to the geometrical characteristics of local structures in the manufacturing process, for example, the complex reinforcing area, the mounting lug boss and other parts can adopt composite materials based on a prepreg resin system, and the outer side wall plate can adopt composite materials based on an RTM resin system and then is subjected to integral co-curing molding. The method adopts different material systems at different positions through design and process parting, greatly reduces the manufacturing difficulty, and is suitable for forming composite material structural parts with different complexity degrees.
2) The forming process is simple, and the internal quality of the composite material structure is easy to ensure. The resin flows only in the plane or the simple curved surface with simple shape, thereby simplifying the design and the manufacture of the mold, and achieving the purposes of simplifying the flow passage and improving the mold filling efficiency. When the resin is cured, the liquid pressure when the RTM resin is filled can meet the molding requirement of the prepreg part, so that the internal quality of the whole structure is ensured.
3) The molding efficiency is higher, has the cost advantage. The multi-level controllable multi-flow forming method can realize one-time integral forming of a complex structure, and saves the manufacturing period. Meanwhile, only a proper pressure source needs to be provided in the manufacturing implementation process, and complex and expensive forming equipment such as an autoclave and the like is not needed, so that the cost is high.
In a second embodiment of the present invention, a method for manufacturing a grille cover structure is provided, the method comprising:
semi-curing the plurality of longitudinal bars by a pre-forming curing process to form the inner skin;
sequentially laying a plurality of box-shaped pieces in a groove formed by adjacent longitudinal ribs and the inner skin;
forming transverse ribs between adjacent connected box-shaped parts by using prepreg paving layers;
and coating the outer skin on the longitudinal ribs, the transverse ribs and the box-shaped piece.
According to the preparation method of the grille cover body structure provided by the embodiment of the invention, the integral grille cover body forming structure is generated by adopting the grille cover body structure and combining the co-curing forming process method of prepreg lamination and RTM injection process, so that the method has the characteristics of good skin forming quality and high double-sided high precision of the structure, and has the advantage of high-reliability integral manufacturing; and by utilizing the characteristic that the soluble or meltable core mold is well soluble or meltable under certain physical conditions, after the grid interlayer is prepared, the outer skin is laid, so that the grid interlayer is sealed between the inner skin and the outer skin, and finally the integral manufacturing and forming of the grid cover body structure are realized.
The grille cover body structure formed by the preparation method provided by the embodiment of the invention has the characteristic of high bending rigidity of the traditional honeycomb/foam sandwich wall plate, has good in-plane pulling and pressing performance, can realize that the bending rigidity of the cover body is improved by 30% under the condition of equal weight with the honeycomb/foam sandwich wall plate structure, and achieves the dual design purposes of high rigidity and light weight of the structure.
It should be noted that the manufacturing principle and the process method of the grille cover structure provided in this embodiment are similar to the manufacturing method of the grille cover structure, and reference may be made to the above description for relevant points, which are not described herein again.
It should be understood that the above-mentioned embodiments of the present invention are only examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention, and it will be obvious to those skilled in the art that other variations or modifications may be made on the basis of the above description, and all embodiments may not be exhaustive, and all obvious variations or modifications may be included within the scope of the present invention.
Claims (6)
1. A method of making a grille cover structure for use on an aircraft, the grille cover structure comprising:
an inner skin;
an outer skin; and
a plurality of longitudinal bars positioned between the inner skin and the outer skin;
the grille cover structure further includes:
a plurality of box-shaped elements located in the grooves formed by the adjacent longitudinal bars and the inner skin, an
A plurality of transverse ribs which are vertical to the longitudinal ribs and are formed between the adjacent box-shaped parts;
wherein the inner skin is of a different material than the outer skin,
the interlayer structures of the grating cover body structures are relatively independent and are used for dispersing impact pressure;
the box comprises a water-soluble core in a hexahedral structure; and
the prepreg layer is coated on the five surface bodies of the water-soluble mold core;
wherein the surface of the box-shaped piece in contact with the inner skin is not paved;
the preparation method comprises the following steps:
semi-curing the plurality of longitudinal bars by a pre-forming curing process to form the inner skin;
sequentially laying a plurality of box-shaped pieces in a groove formed by adjacent longitudinal ribs and the inner skin;
forming transverse ribs between adjacent connected box-shaped parts by using prepreg paving layers;
and coating the outer skin on the longitudinal ribs, the transverse ribs and the box-shaped piece.
2. Method for producing according to claim 1, characterized in that the outer skin is coated on the longitudinal bars, the transverse bars and the box-shaped elements in a RTM process.
3. The production method according to claim 1,
preparing a water-soluble core of the box-shaped part by using a water-soluble core forming die of the box-shaped part;
laying up prepreg on the surfaces of the five surfaces of the water-soluble mold core by a laying-up process to form a box-shaped part;
vacuum bagging to cure the box;
perforating the outer side surface opposite to the unpaved surface of the box-shaped part, and injecting a core solvent into the box-shaped part to form a hollow prepreg box-shaped part;
and filling the open holes of the box-shaped part by using a prepreg patch process to form a closed box-shaped part.
4. The method of manufacturing according to claim 1, wherein the outer skin is a fabric preform.
5. The preparation method according to claim 1, wherein the materials of the longitudinal bars, the transverse bars and the inner skin are unidirectional prepreg laying structures.
6. The production method according to claim 1, wherein the prepreg is formed of a fiber reinforcement material and a resin matrix material.
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| CN112571824B (en) * | 2020-10-27 | 2022-04-08 | 成都飞机工业（集团）有限责任公司 | Layering method for composite material longitudinal and transverse reinforced frame-shaped structure based on RTM (resin transfer molding) |
| CN112571836B (en) * | 2020-11-27 | 2022-10-11 | 长春长光宇航复合材料有限公司 | Preparation method of composite material with embedded metal part closed-cavity grid frame structure |
| CN114179396B (en) * | 2021-12-17 | 2023-07-18 | 江西洪都航空工业集团有限责任公司 | Forming method and die suitable for irregular U-shaped composite material foam sandwich structural member |
| CN114589980A (en) * | 2022-01-28 | 2022-06-07 | 江苏三强复合材料有限公司 | Structure heat-proof integrated double-faced skin grid structure and preparation method thereof |
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| CN101112795A (en) * | 2007-08-31 | 2008-01-30 | 哈尔滨玻璃钢研究院 | Method for preparation of fibre reinforcement resin radicle composite material transmission shafts |
| CN102146196B (en) * | 2011-01-27 | 2012-05-09 | 北京玻钢院复合材料有限公司 | Preparation method of high damping epoxy resin composite |
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