CN115782241A - Method for integrally forming full-composite structural framework in aircraft cabin - Google Patents
Method for integrally forming full-composite structural framework in aircraft cabin Download PDFInfo
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- CN115782241A CN115782241A CN202211519148.7A CN202211519148A CN115782241A CN 115782241 A CN115782241 A CN 115782241A CN 202211519148 A CN202211519148 A CN 202211519148A CN 115782241 A CN115782241 A CN 115782241A
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The invention discloses an integral forming method of a full-composite structural framework in an aircraft cabin in the composite field, wherein the structural framework comprises a framework front structure, a framework rear structure and a reinforcing rib structure for connecting the framework front structure and the framework rear structure, and the integral forming method comprises the following steps: 1) Paving; respectively molding the reinforcing rib structure, the framework front structure and the framework rear structure; 2) Closing the mold; firstly, the framework front structure and the reinforcing rib structure are matched, the outer surfaces of the framework front structure and the reinforcing rib structure are subjected to whole paving, then the whole paved structure and the framework rear structure are matched, and then the whole paving is carried out on the outer surfaces of the framework front structure and the reinforcing rib structure to connect the framework front structure and the framework rear structure into a whole; 3) Assembling; placing the conformal pressing plate and manufacturing a vacuum bag; 4) Curing; curing the mixture in an autoclave according to a curing curve; 5) Demolding; opening the tank and demoulding after cooling after curing; 6) Machining; according to the design requirements, the numerical control machine tool is trimmed and holes are made, and the problem that products are unqualified due to the fact that the strengthening ribs and the structural framework are assembled in a glue-rivet combination mode in the prior art is solved.
Description
Technical Field
The invention relates to the technical field of composite materials, in particular to an integral forming method of a full-composite material structure framework.
Background
The weight of the advanced composite material for aviation can be reduced by 20 to 30 percent correspondingly when the advanced composite material is used for aerospace structures, which is an effect that other advanced technologies cannot achieve, so that the advanced composite material is increasingly widely applied in the aerospace field, and one of four aerospace structure materials is rapidly developed after aluminum, steel and titanium. The carbon fiber reinforced material is a marked product in the field of composite materials, has the advantages of anisotropy (designability), high specific strength, high specific modulus, corrosion resistance, fatigue resistance and the like, has good flexibility in design, can reduce the weight of a structure on the premise of meeting the requirements of rigidity, strength and fatigue performance, and has obvious advantages in the field of aerospace structure design.
In the prior art, there is an airplane cabin interior structure skeleton, the structure of which is shown in fig. 2-3, and which includes a skeleton front structure 101, a skeleton rear structure 102, and a reinforcing rib structure 103 connecting the skeleton front structure 101 and the skeleton rear structure 102, and the structure is made of metal material, and in order to achieve overall weight reduction, the structure needs to be made of composite material; the design of the reinforcing rib structure 103 can enhance the strength and rigidity of the product to a great extent, save the material consumption, reduce the weight and reduce the cost. Steel construction strengthening rib accessible welded connection, carbon fiber strengthening rib structure use the mode installation that glue riveting combines usually, if the misoperation when glue riveting combines, can lead to the product to produce defects such as layering to influence the effect that the strengthening rib can play.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a method for integrally forming a full-composite structural framework in an aircraft cabin, which solves the problem that the product is unqualified because a glue-rivet combination mode is adopted for assembling a reinforcing rib and the structural framework in the prior art.
The purpose of the invention is realized as follows: a method for integrally forming a full-composite structural framework in an aircraft cabin, wherein the structural framework comprises a framework front structure, a framework rear structure and a reinforcing rib structure for connecting the framework front structure and the framework rear structure, and the method comprises the following steps of:
step 1), paving and pasting; respectively molding the reinforcing rib structure, the framework front structure and the framework rear structure;
forming a reinforcing rib structure, namely paving and attaching a half of layers of prepreg on a reinforcing rib mould according to design requirements, then completely paving another half of prepreg on the outer surface of the reinforcing rib mould, and manufacturing a vacuum bag after paving and attaching, and filling the vacuum bag into a tank for precuring;
paving a framework front structure, paving prepreg on a framework front mould according to design requirements, placing an embedded part when the number of layers is half that of the framework front mould, paving the rest prepreg, and manufacturing a vacuum bag to enter a tank for precuring after paving;
paving a framework rear structure, paving prepreg on a framework rear mould according to design requirements, and manufacturing a vacuum bag after paving and precuring;
step 2), die assembly; firstly, the framework front structure and the reinforcing rib structure are matched, the outer surfaces of the framework front structure and the reinforcing rib structure are subjected to whole paving, then the whole paved structure and the framework rear structure are matched, and then the whole paving is carried out on the outer surfaces of the framework front structure and the reinforcing rib structure to connect the framework front structure and the framework rear structure into a whole;
step 3), assembling; placing the conformal pressing plate and manufacturing a vacuum bag;
step 4), curing; curing the mixture in an autoclave according to a curing curve;
step 5), demolding; opening the tank and demoulding after cooling after curing;
step 6), machining; and trimming and drilling holes on the numerical control machine according to design requirements.
As a further limitation of the present invention, the step 1) of forming the reinforcement rib structure specifically includes:
step 1-1) dividing a reinforcing rib mould into a plurality of block-shaped moulds which can be connected in series, processing grooves corresponding to reinforcing rib structures on two sides of the mould, paving a half of layers of prepreg along the grooves, the upper surface and the rear surface, and performing precuring after paving;
and 1-2) connecting a plurality of moulds paved with the prepreg together in series by using connecting rods, adhering the side surfaces of every two moulds together to ensure that the side surfaces of the prepreg are tightly attached, then completely paving the other half layers of prepreg along the top surface of the prepreg and the surfaces of the prepreg outside the moulds at two ends, and pre-curing after paving. By the method, the structure of the reinforcing rib can be laid out and has better structural integrity, so that the strength is ensured.
As a further limitation of the present invention, the step 2) of clamping the mold body comprises:
step 2-1), the top surface of a reinforcing rib mold paved with prepreg is jointed with the bottom surface of a framework front mold paved with prepreg in a fitting manner, and then the whole prepreg paving is carried out on the surfaces except the jointed surface;
and 2-2) attaching and butting the rear end face of the structure obtained in the step 2-1) with the front end face of the framework rear mould on which the prepreg is paved, and then completely paving the prepreg on the surface except the butting surface.
As a further limitation of the present invention, the connection mode between the reinforcement rib mold and the framework front mold in step 2-1) is as follows: the connection is completed by processing a flanging on one of the reinforcing rib molds, processing positioning holes on the flanging and the framework front mold and matching with a positioning screw. The design can ensure the precision of the reinforcing rib mold and the framework front mold during mold closing and the precision of the whole paving process.
As a further limitation of the present invention, in the step 2-2), the connection mode of the framework front mold and the framework rear mold is as follows: a connecting boss is designed in the center of the rear end face of the framework front mold, positioning holes are machined in the connecting boss and the front end face of the framework rear mold, and the connecting boss and the framework rear mold are matched with positioning screws to complete connection. The design can ensure the precision of the framework rear mould and the framework front mould when the moulds are combined, and can ensure the precision of the whole paving.
As a further limitation of the present invention, the parameters of the pre-curing in step 1) are: the pre-compaction temperature is controlled between 60 ℃ and 90 ℃, the heat preservation time is at least 90min, and the external pressure is controlled between 0.1 MPa and 0.6 MPa.
As a further limitation of the invention, the angle of the skeleton anterior structure in step 1) is set according to [45/0/-45/90]] ns And (6) paving and pasting.
As a further limitation of the invention, the angle of the back structure of the skeleton in the step 1) is set according to [45/0/-45/90]] ns And (6) paving and pasting.
Compared with the prior art, the invention has the beneficial effects that:
(1) The framework structure manufactured by the invention saves the glue riveting process, and the structure is more stable;
(2) Compared with the traditional assembly structure, the multi-reinforcement framework structure manufactured by the invention is formed in one step, so that the manpower resource is saved, the operation steps are reduced, the use of the autoclave can be reduced, the energy consumption is further reduced, meanwhile, only one mold is needed, the production cost is reduced, the stability of the assembly structure is matched, and the stability of the integrally formed assembly structure is higher.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
FIG. 1 is a schematic flow chart of the present invention.
Fig. 2 is a first schematic view of the framework structure of the full-composite structure in the aircraft cabin.
Fig. 3 is a schematic diagram of a framework structure of a full-composite structure in an aircraft cabin.
FIG. 4 is a perspective view of the mold used in the present invention.
FIG. 5 is a schematic structural view of a reinforcement rib mold used in the mold of the present invention.
FIG. 6 is a schematic view of a mold structure for a front frame of a mold according to the present invention.
FIG. 7 is a schematic view of the mold structure after the use of the skeleton in the mold according to the present invention.
Fig. 8 is a schematic view of the reinforcing rib mold in the invention.
FIG. 9 is a schematic view of the mold clamping of the present invention.
Fig. 10 is a schematic view of the front framework mold and the reinforcing rib mold in fig. 9 after being closed and laid.
Fig. 11 is a schematic diagram of the matched mold and the framework mold and the paving in fig. 10.
The structure comprises a structure framework 1, a framework front structure 101, a framework rear structure 102, a reinforcing rib structure 103, a mold 2, a framework front mold 201, an embedded part groove 2011, a 2012 connecting boss, a framework rear mold 202, a 2021 molded surface groove, a reinforcing rib mold 203, a reinforcing rib mold 2031 small, a 2032 triangular groove, a 2033 connecting hole and a 2034 flanging structure.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1, the method for integrally forming the full-composite structural framework in the aircraft cabin includes, as shown in fig. 2 to 3, a structural framework 1 including a framework front structure 101, a framework rear structure 102, and a reinforcing rib structure 103 connecting the framework front structure 101 and the framework rear structure 102, and includes the following steps:
(1) Prepreg blanking
And respectively manufacturing blanking graphs of the reinforcing ribs and the front and the back of the framework by using a CPD (compact peripheral device) module of Catia software, and cutting the material sheets by using an automatic blanking machine.
(2) Preparation of the mold 2
When a new mold 2 arrives at a factory, the oil seal of the mold 2 needs to be removed (after the tool is cleaned by gasoline, the mold is cleaned by acetone for three times), then the molded surface of the mold 2 is confirmed to be free of damage, and finally the scribed line is confirmed. Before use, a release agent is coated every time, the new die 2 needs to be wiped for 8-10 times at intervals of 15min, and the used die 2 only needs to be wiped for 3 times; as shown in fig. 4, the mold 2 includes three parts, which are respectively a reinforcing rib mold 2032, a framework front mold 201, and a framework rear mold 2022, and outer sheathing plates are further disposed on the peripheries of the three parts;
as shown in fig. 5, the reinforcing rib mold 2032 is formed by connecting five small reinforcing rib molds 20312 in series, triangular grooves 2032 (a specific shape can be selected according to actual needs) are formed on two sides of each small reinforcing rib mold 20312, two connecting holes 2033 are formed on each small reinforcing rib mold 20312, connecting rods (not shown in the figure) connecting the five small reinforcing rib molds 20312 in series are arranged in the connecting holes 2033, a flange structure 2034 is formed on one small reinforcing rib mold 20312 so as to be attached to the framework front mold 201, positioning holes are correspondingly formed on the two small reinforcing rib molds 20312, and the two small reinforcing rib molds are connected and fixed by positioning bolts;
as shown in fig. 6, the framework front mold 201 is a square block structure, embedded part grooves 2011 are formed in the top, bottom, left and right surfaces of the framework front mold, prepreg for molding is correspondingly laid and attached to the rear end face in a matching manner, a connecting boss 2012 for connecting the framework rear mold 2022 is formed on the rear end face, positioning holes are correspondingly formed in the connecting boss 2012 and the framework rear mold 2022, and the connecting boss 2012 and the framework rear mold 2022 are connected and fixed through positioning bolts;
as shown in fig. 7, the rear framework mold 2022 has a square block structure, and profile grooves 2021 are formed on the bottom, front, left, and right surfaces of the rear framework mold for laying and molding prepreg.
(3) Reinforcing rib paving layer
As shown in fig. 8, half of the layers of prepreg are laid on five small reinforcing rib molds 20312 according to design requirements, the laying angle is laid according to design, and the prepreg is connected in a butt joint mode; after the paving and the pasting are finished, the vacuum bag is manufactured and put into a tank for pre-compaction, the pre-compaction temperature is controlled to be between 60 and 90 ℃, the heat preservation time is at least 90min, and the external pressure is controlled to be between 0.1 and 0.6 MPa.
(4) Reinforcing rib area die 2 assembly
After the reinforcing ribs are cold-pressed, the connecting rods are matched in series and combined through the sequence of the codes of each die 2, the two sides of the reinforcing ribs are jointed to form the reinforcing ribs, and the other half of layers of prepreg are paved after the dies 2 are combined, as shown in fig. 8. After the paving and the pasting are finished, the vacuum bag is manufactured and put into a tank for pre-compaction, the pre-compaction temperature is controlled to be between 60 and 90 ℃, the heat preservation time is at least 90min, and the external pressure is controlled to be between 0.1 and 0.6 MPa.
(5) Front paving plaster for framework
Paving and pasting prepreg on the top, bottom, left, right and rear five surfaces of the framework front mold 201, paving and pasting the prepreg to half thickness according to a paving angle of [45/0/-45/90] ]ns, placing an embedded part, and finally finishing paving and pasting the residual prepreg; after the paving and the pasting are finished, the vacuum bag is manufactured and put into a tank for pre-compaction, the pre-compaction temperature is controlled to be between 60 and 90 ℃, the heat preservation time is at least 90min, and the external pressure is controlled to be between 0.1 and 0.6 MPa.
(6) Rear paving paste for framework
Paving prepreg on the bottom, the front, the left and the right of the framework rear mould 2022, and butting and paving at a paving angle of [45/0/-45/90] ns; after the paving is finished, the vacuum bag is manufactured, the vacuum bag is put into a tank and pre-compacted, the pre-compaction temperature is controlled to be between 60 and 90 ℃, the heat preservation time is at least 90min, and the external pressure is controlled to be between 0.1 and 0.6 MPa.
(7) Die assembly
As shown in fig. 9-11, the bottom surface of the cold-pressed framework front mold 201 is butted with the top surface of the reinforcing rib mold 2032, the small reinforcing rib mold 20312 with a turned edge is used for completing the assembling and positioning with the framework front mold 201 during the butting, and then the whole paving is carried out along the top, the left and the right surfaces of the two butting molds 2, so that the connection strength of the reinforcing rib and the framework front structure 101 can be enhanced, the framework front structure 101 is used as a main bearing unit in the actual use process, the reinforcing rib is used as a reinforcing unit, and a positive layer is arranged between the reinforcing rib and the framework front structure 101, so that the connection strength of the reinforcing rib and the framework front structure 101 can be greatly improved, and the function of the reinforcing rib can be exerted to the maximum extent; after the whole paving is finished, the framework is butted with the framework rear die 2022, the connecting bosses 2012 are used for assembling and positioning during the butting, then the whole paving is carried out along the left and right sides, and the front, the rear and the reinforcing rib areas of the framework are connected into a whole, so that the supporting efficiency of the reinforcing ribs can be further improved.
(8) Assembling
Placing the conformal pressing plate, and making a vacuum bag.
(9) Curing
And (5) putting the product into an autoclave for curing according to a curing curve and recording the real-time process.
(10) Demoulding
After the curing process is finished, opening the tank after the temperature of the die 2 is reduced to below 60 ℃, and cooling the die 2 to room temperature for demoulding.
(11) Nondestructive testing
It was tested for non-detection.
(11) Machining machine
And (5) after the product comes out, the numerical control machine tool is used for trimming and drilling.
The above description of the embodiments is only intended to facilitate the understanding of the method of the invention and its core idea. It should be noted that, for those skilled in the art, without departing from the principle of the present invention, it is possible to make various improvements and modifications to the present invention, and those improvements and modifications also fall within the scope of the claims of the present invention.
Claims (8)
1. The method for integrally forming the full-composite structural framework in the aircraft cabin comprises a framework front structure, a framework rear structure and a reinforcing rib structure for connecting the framework front structure and the framework rear structure, and is characterized by comprising the following steps of:
step 1), paving and pasting; respectively molding the reinforcing rib structure, the framework front structure and the framework rear structure;
forming a reinforcing rib structure, namely paving and pasting a half of layers of prepreg on a reinforcing rib mould according to design requirements, then completely paving another half of layers of prepreg on the outer surface of the reinforcing rib mould, and after paving and pasting are finished, manufacturing a vacuum bag, filling into a tank and precuring;
paving a framework front structure, paving prepreg on a framework front mould according to design requirements, placing an embedded part when the number of layers is half that of the framework front mould, paving the rest prepreg, and manufacturing a vacuum bag to enter a tank for precuring after paving;
paving a framework rear structure, paving a prepreg on a framework rear mould according to design requirements, and manufacturing a vacuum bag after paving and precuring;
step 2), die assembly; firstly, the framework front structure and the reinforcing rib structure are matched, the outer surfaces of the framework front structure and the reinforcing rib structure are integrally paved, then the integrally paved structure and the framework rear structure are matched, and the integrally paved structure and the framework rear structure are connected into a whole;
step 3), assembling; placing the conformal pressing plate and manufacturing a vacuum bag;
step 4), curing; curing the mixture in an autoclave according to a curing curve;
step 5), demolding; after curing, cooling, opening the tank and demoulding;
step 6), machining; and trimming and drilling holes on the numerical control machine according to design requirements.
2. The method for integrally forming the full-composite structural framework in the aircraft cabin according to claim 1, wherein the concrete step of forming the reinforcing rib structure in the step 1) comprises:
step 1-1) dividing a reinforcing rib mould into a plurality of block-shaped moulds which can be connected in series, processing grooves corresponding to reinforcing rib structures on two sides of the mould, paving a half of layers of prepreg along the grooves, the upper surface and the rear surface, and performing precuring after paving;
and 1-2) connecting a plurality of moulds paved with prepreg in series by using connecting rods, jointing the side surfaces of every two moulds together to ensure that the side surfaces of the prepreg are tightly attached, then paving the other half of layers of prepreg along the top surface of the prepreg and the surfaces of the prepreg outside the moulds at two ends, and pre-curing after paving.
3. The method for integrally forming the full-composite structural framework in the aircraft cabin according to claim 1 or 2, wherein the step 2) of clamping the mold body comprises the following steps:
step 2-1), the top surface of the reinforcing rib mold paved with the prepreg is jointed with the bottom surface of the framework front mold paved with the prepreg in a fitting manner, and then the prepreg is completely paved on the surface except the jointed surface;
and 2-2) attaching and butting the rear end face of the structure obtained in the step 2-1) with the front end face of the framework rear mould on which the prepreg is paved, and then completely paving the prepreg on the surface except the butting surface.
4. The method for integrally forming the full-composite structural framework in the aircraft cabin according to claim 3, wherein the connection mode of the reinforcement rib mold and the framework front mold in the step 2-1) is as follows: the connection is completed by processing a flanging on one of the reinforcing rib molds, processing positioning holes on the flanging and the framework front mold and matching with a positioning screw.
5. The method for integrally forming the full-composite-material-structure framework in the aircraft cabin according to claim 3, wherein in the step 2-2), the connection mode of the framework front mold and the framework rear mold is as follows: a connecting boss is designed in the center of the rear end face of the framework front mold, positioning holes are machined in the connecting boss and the front end face of the framework rear mold, and the connecting boss and the framework rear mold are matched with positioning screws to complete connection.
6. The method for integrally forming the full composite material structural framework in the aircraft cabin according to claim 1 or 2, wherein the parameters of the pre-curing in the step 1) are as follows: the pre-compaction temperature is controlled between 60 ℃ and 90 ℃, the heat preservation time is at least 90min, and the external pressure is controlled between 0.1 MPa and 0.6 MPa.
7. The method for integrally forming the framework of the full-composite structure in the airplane cabin according to claim 1 or 2, wherein the paving angle of the framework front structure in the step 1) is [45/0/-45/90]] ns And (6) paving and pasting.
8. The method for integrally forming the framework of the full-composite structure in the aircraft cabin according to claim 1 or 2, wherein the paving angle of the framework rear structure in the step 1) is [45/0/-45/90]] ns And (6) paving and pasting.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211519148.7A CN115782241A (en) | 2022-11-30 | 2022-11-30 | Method for integrally forming full-composite structural framework in aircraft cabin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211519148.7A CN115782241A (en) | 2022-11-30 | 2022-11-30 | Method for integrally forming full-composite structural framework in aircraft cabin |
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| Publication Number | Publication Date |
|---|---|
| CN115782241A true CN115782241A (en) | 2023-03-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211519148.7A Withdrawn CN115782241A (en) | 2022-11-30 | 2022-11-30 | Method for integrally forming full-composite structural framework in aircraft cabin |
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| Country | Link |
|---|---|
| CN (1) | CN115782241A (en) |
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2022
- 2022-11-30 CN CN202211519148.7A patent/CN115782241A/en not_active Withdrawn
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