CN115388715A - Light missile wing structure and forming method - Google Patents
Light missile wing structure and forming method Download PDFInfo
- Publication number
- CN115388715A CN115388715A CN202210912538.4A CN202210912538A CN115388715A CN 115388715 A CN115388715 A CN 115388715A CN 202210912538 A CN202210912538 A CN 202210912538A CN 115388715 A CN115388715 A CN 115388715A
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- China
- Prior art keywords
- wing
- cavity
- foam block
- wall
- die
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/04—Stabilising arrangements using fixed fins
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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
- B29C44/00—Shaping by internal pressure generated in the material, e.g. swelling or foaming ; Producing porous or cellular expanded plastics articles
- B29C44/02—Shaping by internal pressure generated in the material, e.g. swelling or foaming ; Producing porous or cellular expanded plastics articles for articles of definite length, i.e. discrete articles
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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
- B29C44/00—Shaping by internal pressure generated in the material, e.g. swelling or foaming ; Producing porous or cellular expanded plastics articles
- B29C44/02—Shaping by internal pressure generated in the material, e.g. swelling or foaming ; Producing porous or cellular expanded plastics articles for articles of definite length, i.e. discrete articles
- B29C44/12—Incorporating or moulding on preformed parts, e.g. inserts or reinforcements
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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
- B29C44/00—Shaping by internal pressure generated in the material, e.g. swelling or foaming ; Producing porous or cellular expanded plastics articles
- B29C44/34—Auxiliary operations
- B29C44/60—Measuring, controlling or regulating
Abstract
The invention discloses a light missile wing structure, which comprises a wing handle and a thin-wall wing surface connected with the wing handle, wherein a front cavity, a middle cavity and a rear cavity are formed between the top wall and the bottom wall of an inner cavity of the thin-wall wing surface through a front beam and a rear beam, the front beam and the rear beam are integrally formed with the upper wall and the lower wall of the thin-wall wing surface, and a front edge foam block, a middle foam block and a rear edge foam block are respectively filled in the front cavity, the middle cavity and the rear cavity. The beneficial effects are that: the light elastic wing structure combines the advantages of a beam structure and a foam sandwich structure, and overcomes the defects of light weight limitation, easy instability of skin and weak bending resistance at the wing handle of the common foam sandwich structure. Meanwhile, the light missile wing forming method disclosed by the invention has the advantages that the foam core is made by rapid foaming forming, the problem that the common foam sandwich structure needs to be carved in advance is avoided, the processing cost and the material waste are reduced, and the surface of the formed missile wing does not need to be coated.
Description
Technical Field
The invention relates to the technical field of missile wing structures, in particular to a light missile wing structure and a forming method.
Background
The missile wing is a main load-bearing structural member of the missile, and needs to have enough strength and rigidity, and meanwhile, the light weight of the missile wing has obvious effects of improving the flying speed of the missile and improving the range, and the light missile wing structure and the forming method are adopted. At present, the lightweight missile wing is mainly formed by adopting a carbon fiber composite material and adopts a beam structure and a foam sandwich structure. The beam type structure needs a preformed structural beam, secondary bonding is adopted, and the light weight effect is limited; the foam sandwich structure is easy to have the conditions of insufficient rigidity and overlarge loading deflection of the missile wing in a wing handle transition region.
In addition, in the conventional carbon fiber prepreg compression molding process, many pores are generated on the surface of the missile wing, so that surface coating treatment is required, and the light weight effect is reduced.
Disclosure of Invention
The invention aims to provide a light missile wing structure and a forming method, and provides a forming method with a coating-free surface, so that the optimal light weight effect is achieved on the premise of ensuring that the function and the bearing performance of the missile wing structure are not changed.
The technical scheme of the invention is realized as follows:
a light missile wing structure comprises a wing handle and a thin-wall wing surface connected with the wing handle, wherein a front cavity, a middle cavity and a rear cavity are formed between the top wall and the bottom wall of an inner cavity of the thin-wall wing surface through a front beam and a rear beam, the front beam and the rear beam are integrally formed with the upper wall and the lower wall of the thin-wall wing surface, and a front edge foam block, a middle foam block and a rear edge foam block are respectively filled in the front cavity, the middle cavity and the rear cavity.
Furthermore, a central mounting hole and a position control hole are formed in the wing handle and are used for assembling the missile wing and positioning the missile wing after rotation during flying.
Furthermore, the front beam and the rear beam are of flat plate structures and are used for bearing bending moment loads and ensuring the bending rigidity of the connection part of the front beam and the rear beam and the wing handle.
A forming method of a light missile wing structure comprises the following steps:
step S1: preparing a foam preformed body: weighing the foaming adhesive film according to the weight, putting the foaming adhesive film into a die cavity of a steel die or an aluminum die preforming body die, heating to 60-80 ℃ after die assembly, preserving heat for 30-60min, carrying out primary foaming molding on a preforming body of a front edge foam block, a middle foam block and a rear edge foam block, and taking out the foam blocks after shaping;
step S2: applying carbon fiber prepreg to the inner cavities of the upper die and the lower die of the missile wing forming die in a vacuum adsorption mode;
and step S3: applying carbon fiber prepreg on the preformed foam block, wrapping the surface of the foam block completely, and then placing the foam block into a die cavity of a missile wing forming die;
and step S4: after the die is closed, uniformly heating the die to 120-150 ℃, and carrying out secondary foaming on the foam block pre-forming body to generate an expansion force, so that the interlaminar compactness after the carbon fiber prepreg is cured and formed is ensured, and air holes on the surface layer of the carbon fiber prepreg are removed;
step S5: preserving heat for 1-2 hours, cooling to normal temperature, opening the mold and taking out the product;
step S6: the pilot hole and the inside special-shaped structure of wing handle adopt CNC processing to acquire.
Further, the temperature rise rate in the step S4 is 1 ℃/min, and the temperature drop rate in the step S5 is 0.2-1 ℃/min.
The invention has the beneficial effects that: the light elastic wing structure combines the advantages of a beam structure and a foam sandwich structure, and overcomes the defects of light weight limitation, easy instability of skin and weak bending resistance at the wing handle of the common foam sandwich structure of the common beam structure.
Meanwhile, according to the light missile wing forming method, the foam core is made into rapid foaming forming, so that the problem that the common foam sandwich structure needs to be carved in advance is avoided, the processing cost and the material waste are reduced, and the surface of the formed missile wing does not need to be coated. On the basis of ensuring the functions and the strength, the carbon fiber composite material has light weight and strong height, and the foam has high rigidity and low density, so that the weight of the missile wing structure can be reduced by 30 percent.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described 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 without creative efforts.
FIG. 1 is a schematic view of a lightweight missile wing;
FIG. 2 isbase:Sub>A cross-sectional view ofbase:Sub>A lightweight missile wing A-A;
FIG. 3 is a schematic view of a foam molding preform;
fig. 4 is a schematic view of compression molding of the missile wing.
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.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.
According to an embodiment of the invention, a lightweight missile wing structure and a forming method are provided.
Referring to fig. 1-4, a lightweight missile wing structure according to an embodiment of the invention comprises a wing handle 1 and a thin-walled wing surface 2 connected with the wing handle, wherein a front cavity, a middle cavity and a rear cavity are formed between the top wall and the bottom wall of an inner cavity of the thin-walled wing surface 2 through a front beam 3 and a rear beam 4, the front beam 3 and the rear beam 4 are integrally formed with the upper wall and the lower wall of the thin-walled wing surface 2, and the front cavity, the middle cavity and the rear cavity are respectively filled with a front edge foam block 5, a middle foam block 6 and a rear edge foam block 7.
Through the technical scheme: a front cavity, a middle cavity and a rear cavity are formed between the top wall and the bottom wall of the inner cavity of the thin-wall airfoil surface 2 through the front beam 3 and the rear beam 4, and a front edge foam block 5, a middle foam block 6 and a rear edge foam block 7 are respectively filled in the front cavity, the middle cavity and the rear cavity, so that the rigidity of the thin-wall airfoil surface 2 is improved. And the density of the foam core material can be adjusted according to the load condition of the thin-wall airfoil 2.
And a front beam 3 and a rear beam 4 are connected between the top wall and the bottom wall of the inner cavity of the thin-wall airfoil surface 2, mainly bear bending moment load and ensure the bending rigidity of the joint with the wing handle 1.
Furthermore, a central mounting hole 10 and a position control hole 11 are arranged on the wing handle 1 and are used for assembling the missile wing and positioning the missile wing after rotation in flight.
Further, the front beam 3 and the rear beam 4 are of flat plate structures and are used for bearing bending moment loads and ensuring the bending rigidity of the connection part of the wing handle 1.
A method for forming a lightweight missile wing structure comprises the following steps:
step S1: preparing a foam preformed body: weighing the foaming adhesive film according to the weight, putting the foaming adhesive film into a die cavity of a steel die or an aluminum die preforming body die 8, heating to 60-80 ℃ after die assembly, preserving heat for 30-60min, carrying out primary foaming molding on a preforming body of a front edge foam block 5, a middle foam block 6 and a rear edge foam block 7, and taking out the foam blocks after shaping;
step S2: applying carbon fiber prepreg to the inner cavities of the upper die and the lower die of the missile wing forming die 9 in a vacuum adsorption mode;
and step S3: applying carbon fiber prepreg on the preformed foam block, wrapping the surface of the foam block completely, and then placing the foam block into a die cavity of a missile wing forming die 9;
and step S4: after the die is closed, uniformly heating the die to 120-150 ℃, and carrying out secondary foaming on the foam block pre-forming body to generate an expansion force, so that the interlaminar compactness after the carbon fiber prepreg is cured and formed is ensured, and air holes on the surface layer of the carbon fiber prepreg are removed;
step S5: preserving heat for 1-2 hours, cooling to normal temperature, opening the die and taking out the product;
step S6: the pilot hole and the inside special-shaped structure of wing handle 1 adopt CNC processing to obtain.
Further, the temperature rise rate in the step S4 is 1 ℃/min, and the temperature drop rate in the step S5 is 0.2-1 ℃/min.
In the step S1, after die assembly, heating to 60-80 ℃, heating the foaming adhesive film to expand the foaming adhesive film into a hard block body, and preserving heat for 30-60min for expansion and shaping.
In the step S2, specifically, carbon fiber prepreg is laid in the upper die cavity and the lower die cavity, the upper die is covered on the lower die and is sent into a heating plate of a hot press, and a vacuum pump is always turned on during heating to realize vacuum adsorption.
In the step S4, the foam preformed body is foamed for the second time to generate larger expansion force, so that the layers of the carbon fiber prepreg after curing and molding are compact, air holes on the surface layer of the carbon fiber prepreg are eliminated, the compactness in the compounding process of the carbon fiber prepreg is improved, the surface layer of the composite material of the missile wing is smooth and clean, and coating treatment is not needed.
In addition, the foaming adhesive film is HR thermal self-expansion high-energy adhesive. The formed mould is a steel mould or an aluminum mould. The wing handle assembly hole and the inner special-shaped structure are obtained by CNC machining.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.
Claims (5)
1. A light missile wing structure comprises a wing handle (1) and a thin-wall wing surface (2) connected with the wing handle, and is characterized in that a front cavity, a middle cavity and a rear cavity are formed between the top wall and the bottom wall of an inner cavity of the thin-wall wing surface (2) through a front beam (3) and a rear beam (4), the front beam (3) and the rear beam (4) are integrally formed with the upper wall and the lower wall of the thin-wall wing surface (2), and a front edge foam block (5), a middle foam block (6) and a rear edge foam block (7) are respectively filled in the front cavity, the middle cavity and the rear cavity.
2. A lightweight missile wing structure according to claim 1, characterized in that the wing handle (1) is provided with a central mounting hole (10) and a position control hole (11) for installation and post-rotation positioning of the missile wing in flight.
3. A lightweight missile wing structure according to claim 1, characterized in that the front beam (3) and the rear beam (4) are flat plate structures and are used for bearing bending moment load and ensuring the bending rigidity at the connection part with the wing handle (1).
4. A forming method of a light missile wing structure is characterized by comprising the following steps:
step S1: preparing a foam preformed body: weighing the foaming adhesive film according to the weight, putting the foaming adhesive film into a mold cavity of a steel mold or aluminum mold preformed body mold (8), heating to 60-80 ℃ after mold closing, preserving heat for 30-60min, carrying out primary foaming molding on preformed bodies of a front edge foam block (5), a middle foam block (6) and a rear edge foam block (7), and taking out the foam blocks after shaping;
step S2: applying carbon fiber prepreg to the inner cavities of the upper die and the lower die of the missile wing forming die (9) in a vacuum adsorption mode;
and step S3: applying carbon fiber prepreg on the preformed foam block, wrapping the surface of the foam block completely, and then placing the foam block into a die cavity of a missile wing forming die (9);
and step S4: after the die is closed, uniformly heating the die to 120-150 ℃, and carrying out secondary foaming on the foam block pre-forming body to generate an expansion force, so that the interlaminar compactness after the carbon fiber prepreg is cured and formed is ensured, and air holes on the surface layer of the carbon fiber prepreg are removed;
step S5: preserving heat for 1-2 hours, cooling to normal temperature, opening the mold and taking out the product;
step S6: the assembling hole and the internal special-shaped structure of the wing handle (1) are obtained by CNC machining.
5. The method for forming a lightweight missile wing structure according to claim 4, wherein the temperature rise rate in the step S4 is 1 ℃/min and the temperature decrease rate in the step S5 is 0.2-1 ℃/min.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210912538.4A CN115388715A (en) | 2022-07-30 | 2022-07-30 | Light missile wing structure and forming method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210912538.4A CN115388715A (en) | 2022-07-30 | 2022-07-30 | Light missile wing structure and forming method |
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| Publication Number | Publication Date |
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| CN115388715A true CN115388715A (en) | 2022-11-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210912538.4A Pending CN115388715A (en) | 2022-07-30 | 2022-07-30 | Light missile wing structure and forming method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116858036A (en) * | 2023-09-04 | 2023-10-10 | 北京爱思达航天科技有限公司 | Ultrathin light composite material flying wing and preparation method thereof |
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| US5222297A (en) * | 1991-10-18 | 1993-06-29 | United Technologies Corporation | Composite blade manufacture |
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| US20160311518A1 (en) * | 2013-11-26 | 2016-10-27 | James P. Wiebe | Wing structure utilizing carbon fiber spar and shaped foam |
| CN106182801A (en) * | 2016-07-15 | 2016-12-07 | 西北工业大学 | A kind of aircraft foam core filled composite material rudder face forming method |
| CN108959744A (en) * | 2018-06-21 | 2018-12-07 | 西安爱生技术集团公司 | A kind of small and medium size unmanned aerial vehicles composite wing wing box manufacturing method |
| CN109470089A (en) * | 2018-11-23 | 2019-03-15 | 江西洪都航空工业集团有限责任公司 | A kind of short beam sandwich mini-bomb wing structure |
| CN113977991A (en) * | 2021-11-16 | 2022-01-28 | 山东恒源兵器科技股份有限公司 | Carbon fiber wing internal foaming forming method |
| CN114001596A (en) * | 2021-11-24 | 2022-02-01 | 长三角先进材料研究院 | RTM (resin transfer molding) integrally-formed composite missile wing with variable joint and manufacturing method thereof |
| CN216245874U (en) * | 2021-11-24 | 2022-04-08 | 长三角先进材料研究院 | RTM integrally-formed composite missile wing with variable joint |
-
2022
- 2022-07-30 CN CN202210912538.4A patent/CN115388715A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4671471A (en) * | 1984-05-21 | 1987-06-09 | Mitchell Wing, Inc. | Foam reinforced aluminum wing structure |
| US5222297A (en) * | 1991-10-18 | 1993-06-29 | United Technologies Corporation | Composite blade manufacture |
| CN101641255A (en) * | 2007-03-26 | 2010-02-03 | 诺瓦化学公司 | Sportsboard structures |
| US20160311518A1 (en) * | 2013-11-26 | 2016-10-27 | James P. Wiebe | Wing structure utilizing carbon fiber spar and shaped foam |
| CN205150216U (en) * | 2015-11-24 | 2016-04-13 | 中国航天时代电子公司 | Unmanned aerial vehicle's foam presss from both sides core wing |
| CN106182801A (en) * | 2016-07-15 | 2016-12-07 | 西北工业大学 | A kind of aircraft foam core filled composite material rudder face forming method |
| CN108959744A (en) * | 2018-06-21 | 2018-12-07 | 西安爱生技术集团公司 | A kind of small and medium size unmanned aerial vehicles composite wing wing box manufacturing method |
| CN109470089A (en) * | 2018-11-23 | 2019-03-15 | 江西洪都航空工业集团有限责任公司 | A kind of short beam sandwich mini-bomb wing structure |
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| CN114001596A (en) * | 2021-11-24 | 2022-02-01 | 长三角先进材料研究院 | RTM (resin transfer molding) integrally-formed composite missile wing with variable joint and manufacturing method thereof |
| CN216245874U (en) * | 2021-11-24 | 2022-04-08 | 长三角先进材料研究院 | RTM integrally-formed composite missile wing with variable joint |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116858036A (en) * | 2023-09-04 | 2023-10-10 | 北京爱思达航天科技有限公司 | Ultrathin light composite material flying wing and preparation method thereof |
| CN116858036B (en) * | 2023-09-04 | 2023-12-29 | 北京爱思达航天科技有限公司 | Ultrathin light composite material flying wing and preparation method thereof |
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