CN109605780B - Method for integrally forming composite material structure of unmanned aerial vehicle - Google Patents
Method for integrally forming composite material structure of unmanned aerial vehicle Download PDFInfo
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- CN109605780B CN109605780B CN201811385114.7A CN201811385114A CN109605780B CN 109605780 B CN109605780 B CN 109605780B CN 201811385114 A CN201811385114 A CN 201811385114A CN 109605780 B CN109605780 B CN 109605780B
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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
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing 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
- 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
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3079—Cockpits, canopies
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3082—Fuselages
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3085—Wings
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention belongs to the field of composite material structure forming, and particularly relates to a method for integrally forming an unmanned aerial vehicle composite material structure; according to the method, mold materials with different expansion coefficients are respectively used as a male mold and a female mold of the unmanned aerial vehicle mold, fiber materials are laid between the male mold and the female mold, and a huge deformation difference is generated due to different expansion coefficients of the male mold and the female mold during heating, so that the fiber materials forming the unmanned aerial vehicle body structure are cured and formed at high temperature and high pressure, and finally the unmanned aerial vehicle formed by one-step curing is obtained. The method can be used for heating and forming the unmanned aerial vehicle body in one step without secondary curing, so that the manufacturing and assembling cost is reduced, and the difficulty of a designer in designing the unmanned aerial vehicle body structure is reduced.
Description
Technical Field
The invention belongs to the field of composite material structure forming, and particularly relates to an integral forming method of an unmanned aerial vehicle composite material structure.
Background
At present, most of composite material forming processes are die pressing, vacuum bag pressing and the like, and when a multi-characteristic unmanned aerial vehicle body (a fuselage cabin body and a multi-rib beam wing) is prepared, a design is usually carried out by adopting two parts of a split half die to manufacture. The manufacturing process comprises the steps of firstly curing the upper skin and the lower skin, and carrying out secondary curing through folding connection or co-cementation after molding, and the process method increases the manufacturing cost and simultaneously causes the step at the surface seam of the machine body, so that the mold closing position is easy to crack.
In the field of aviation manufacturing, after most of domestic unmanned aerial vehicles are made of composite materials and cured and molded, structural parts are connected and assembled. Increase manufacturing and assembly cost, also increase the degree of difficulty of designer when designing unmanned aerial vehicle organism structure.
Disclosure of Invention
In order to solve the problems, the invention provides a method for integrally forming an unmanned aerial vehicle composite material structure, which can be used for heating and forming an unmanned aerial vehicle body at one time without secondary curing, thereby reducing the manufacturing and assembling cost and simultaneously reducing the difficulty of a designer in designing the unmanned aerial vehicle body structure.
The invention is realized by the following technical scheme:
the method adopts mold materials with different expansion coefficients as a male mold and a female mold of an unmanned aerial vehicle mold respectively, fiber materials are laid between the male mold and the female mold, and huge deformation difference is generated due to different expansion coefficients of the male mold and the female mold during heating, so that the fiber materials forming the unmanned aerial vehicle body structure are solidified and molded at high temperature and high pressure, and finally the unmanned aerial vehicle formed by one-step solidification is obtained.
Further, the male die is a first flexible body and a second flexible body which have large expansion coefficients; the female die is made of a metal material with a small expansion coefficient.
Further, the method comprises the following specific contents:
step 1: preparing the first and second flexible bodies
Respectively manufacturing the first flexible body and the second flexible body with complete and flawless surfaces by adopting an unmanned aerial vehicle die or a die specially used for manufacturing the flexible bodies, and taking out the first flexible body and the second flexible body after curing;
step 2: paving fiber material
Respectively paving the fiber materials on the surfaces of a right die, a right die insert, the first flexible body and the second flexible body of a female die in the unmanned aerial vehicle die;
and step 3: die assembly
Folding a left die, a left die insert, a first front die, a second front die, a third front die, an upper die of a female die in the unmanned aerial vehicle die and the right die, the right die insert, the first flexible body and the second flexible body which are paved with the fiber material on the surface in the step 2, locking the folded bodies by using a standard part to achieve the required die locking force, and completing die assembly to obtain an integral part;
and 4, step 4: monolithic heating and forming
The integral piece is only required to be placed in an oven or a press for heating and forming;
after forming, sequentially disassembling an embedded block of a female die in the unmanned aerial vehicle die, the right die insert, the left die insert, the first front die, the second front die, the third front die, the upper die and the standard part, and then taking out a formed unmanned aerial vehicle body, wherein the unmanned aerial vehicle body contains a first flexible body and a second flexible body;
and finally, taking the first flexible body out of the unmanned aerial vehicle body, and keeping the second flexible body in the unmanned aerial vehicle body to increase the rigidity of the unmanned aerial vehicle body, thereby finally obtaining the one-step curing unmanned aerial vehicle.
Further, the material of the first flexible body is a material whose main chain is composed of silicon and oxygen atoms alternately.
Further, the material of the second flexible body is acrylic material.
Further, the fiber material is a carbon fiber composite material or a glass fiber composite material.
Further, the standard component is a screw and nut type component commonly used by those skilled in the art.
Further, the expansion coefficient of the first flexible body is greater than the expansion coefficient of the second flexible body.
Further, the first and second flexible bodies are of different materials.
Further, the integral piece in the step 4 can also be placed in an autoclave for heating and forming.
Further, the fiber material laid in step 2 is used for preparing materials for forming the unmanned aerial vehicle.
Furthermore, the unmanned aerial vehicle mould is a closed space, fiber materials are laid on the inner wall of the unmanned aerial vehicle mould, and the spare positions in the middle of the unmanned aerial vehicle mould are filled with the flexible bodies, so that the flexible bodies follow the shape of the mould, but the flexible bodies are smaller than the mould cavity by one circle, and the circle is used for adhering the fiber materials.
Further, in step 4, the unmanned aerial vehicle is required to have two conditions of temperature and pressure during forming, and the autoclave can provide the two conditions at the same time, but the manufacturing cost is very high, and the advantage of being placed in an oven or a press is that the device does not need to additionally provide pressure, only provides temperature, and the pressure is just from the differential pressure value of the expansion coefficient of the flexible body and the female die after being heated, and the conditions are simple, easy to implement and safer.
The invention has the following beneficial technical effects:
(1) the method for integrally forming the composite material structure of the unmanned aerial vehicle adopts die materials with different expansion coefficients, and utilizes extrusion force generated by different heated volume expansion to apply construction pressure to products. The male die is made of a flexible material with a large expansion coefficient, the female die is made of a metal material with a small expansion coefficient, and the cloth layer is laid between the male die and the female die. When heating, because of the different expansion coefficients of the male and female dies, great deformation difference is generated, so that the body structure is solidified at high temperature and high pressure.
(2) The integral forming method of the unmanned aerial vehicle composite material structure provided by the invention is used for heating and forming once, secondary curing is not needed, the manufacturing and assembling cost is reduced, and meanwhile, when a designer designs the unmanned aerial vehicle body structure, the setting of a process separating surface or the position and the mode of a die closing spigot do not need to be considered, so that the difficulty of the designer in designing the unmanned aerial vehicle body structure is reduced.
(3) The integral forming method of the unmanned aerial vehicle composite material structure can prevent steps from appearing at the surface joint of the one-time heating forming machine and prevent the mold closing position from cracking.
Drawings
Fig. 1 is a schematic cross-sectional side view of a placement position of a flexible body in a method for integrally forming an unmanned aerial vehicle composite structure according to an embodiment of the present invention.
Fig. 2 is a schematic expansion view of an integral part in a method for integrally forming an unmanned aerial vehicle composite structure according to an embodiment of the present invention.
Fig. 3 is a schematic front view of an integral part in the method for integrally forming the composite material structure of the unmanned aerial vehicle according to the embodiment of the invention.
Description of reference numerals: 1-a first flexible body, 2-a second flexible body, 3-a fiber material, 4-an embedded block, 5-a right die, 6-a right die insert, 7-a left die, 8-a left die insert, 9-a first front die, 10-a second front die, 11-a third front die, 12-an upper die and 13-a standard part.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
On the contrary, the invention is intended to cover alternatives, modifications, equivalents and alternatives which may be included within the spirit and scope of the invention as defined by the appended claims. Furthermore, in the following detailed description of the present invention, certain specific details are set forth in order to provide a better understanding of the present invention. It will be apparent to one skilled in the art that the present invention may be practiced without these specific details.
The embodiment provides a method for integrally forming an unmanned aerial vehicle composite material structure, as shown in fig. 1-3, in the method, mold materials with different expansion coefficients are respectively used as a male mold and a female mold of an unmanned aerial vehicle mold, a fiber material 3 is laid between the male mold and the female mold, and a huge deformation difference is generated due to different expansion coefficients of the male mold and the female mold during heating, so that the fiber material 3 forming the unmanned aerial vehicle body structure is cured and formed at high temperature and high pressure, and finally, the unmanned aerial vehicle formed by one-step curing is obtained.
The male die is a first flexible body 1 and a second flexible body 2 with large expansion coefficients; the female die is made of a metal material with a small expansion coefficient.
The method comprises the following specific contents:
step 1: preparing a first flexible body 1 and a second flexible body 2
Respectively manufacturing the first flexible body 1 and the second flexible body 2 with complete and flawless surfaces by adopting an unmanned aerial vehicle die or a die specially used for manufacturing the flexible bodies, and taking out the flexible bodies after curing;
step 2: lay down and paste the fibrous material 3
Respectively paving the fiber material 3 on the surfaces of a right die 5, a right die insert 6, the first flexible body 1 and the second flexible body 2 of a female die in the unmanned aerial vehicle die;
and step 3: die assembly
Folding a left mold 7, a left mold insert 8, a first front mold 9, a second front mold 10, a third front mold 11 and an upper mold 12 of a female mold of the unmanned aerial vehicle mold and the right mold 5, the right mold insert 6, the first flexible body 1 and the second flexible body 2 which are paved with the fiber material 3 on the surfaces in the step 2, locking the folded parts by using a standard part 13 to achieve the required mold locking force, and completing mold closing to obtain an integral part;
and 4, step 4: monolithic heating and forming
The integral piece is only required to be placed in an oven or a press for heating and forming;
after forming, sequentially disassembling the inner embedded block 4 of the female die in the unmanned aerial vehicle die, the right die 5, the right die insert 6, the left die 7, the left die insert 8, the first front die 9, the second front die 10, the third front die 11, the upper die 12 and the standard part 13, and then taking out the formed unmanned aerial vehicle body, wherein the unmanned aerial vehicle body contains the first flexible body 1 and the second flexible body 2;
and finally, taking the first flexible body 1 out of the unmanned aerial vehicle body, and leaving the second flexible body 2 inside the unmanned aerial vehicle body to increase the rigidity of the unmanned aerial vehicle body, thereby finally obtaining the unmanned aerial vehicle molded by one-time curing.
The material of the first flexible body 1 is a material whose main chain is composed of silicon and oxygen atoms alternately.
The material of the second flexible body 2 is acrylic material.
The fiber material 3 is a carbon fiber composite material or a glass fiber composite material.
The standard part 13 is a screw and nut type part commonly used by those skilled in the art.
The first flexible body 1 and the second flexible body 2 are of different materials.
The integral piece in the step 4 can also be placed in an autoclave for heating and forming.
The fiber material 3 laid in step 2 is used for preparing materials for forming the unmanned aerial vehicle.
The unmanned aerial vehicle mould is a closed space, and its inner wall has laid fibre material 3, and the middle vacant position fills up the flexible body, so the flexible body is along with the mould shape, but is less than, the mould die cavity by one circle, and this circle is used for pasting fibre material 3.
In the step 4, two conditions of temperature and pressure are required during unmanned aerial vehicle forming, the autoclave can provide the two conditions at the same time, but the manufacturing cost is high, and the advantage of being placed in an oven or a press is that the equipment does not need to additionally provide pressure, only provides temperature, and the pressure comes from the thermal expansion characteristic of the flexible body, so that the condition is simple, easy to implement and safer.
The method for integrally forming the composite material structure of the unmanned aerial vehicle adopts die materials with different expansion coefficients, and utilizes extrusion force generated by different heated volume expansion to apply construction pressure to products. The male die is made of a flexible material with a large expansion coefficient, the female die is made of a metal material with a small expansion coefficient, and the cloth layer is laid between the male die and the female die. When heating, because of the different expansion coefficients of the male and female dies, great deformation difference is generated, so that the body structure is solidified at high temperature and high pressure. In addition, the method of unmanned aerial vehicle combined material structure integrated into one piece adds thermoforming, need not the secondary cure, has reduced manufacturing and assembly cost, and the designer can need not consider setting for of technology parting surface or the position and the mode of compound die tang when designing unmanned aerial vehicle organism structure simultaneously, has reduced the degree of difficulty of designer when designing unmanned aerial vehicle organism structure. Finally, the surface joint of the unmanned aerial vehicle composite material structure integrally formed by the method can not have steps when being heated once, and the mold closing position can not crack.
Claims (8)
1. The method is characterized in that mold materials with different expansion coefficients are respectively used as a male mold and a female mold of an unmanned aerial vehicle mold, fiber materials are laid between the male mold and the female mold, and when the fiber materials are heated, the fiber materials forming the unmanned aerial vehicle body structure are cured and molded at high temperature and high pressure due to the fact that the male mold and the female mold have different expansion coefficients, and finally the unmanned aerial vehicle which is cured and molded at one time is obtained;
the male die is a first flexible body and a second flexible body which have large expansion coefficients; the female die is made of a metal material with a small expansion coefficient;
the method comprises the following specific contents:
step 1: preparing the first and second flexible bodies
Respectively manufacturing the first flexible body and the second flexible body with complete and flawless surfaces by adopting an unmanned aerial vehicle die or a die specially used for manufacturing the flexible bodies, and taking out the first flexible body and the second flexible body after curing;
step 2: paving fiber material
Respectively paving the fiber materials on the surfaces of a right die, a right die insert, the first flexible body and the second flexible body of a female die in the unmanned aerial vehicle die;
and step 3: die assembly
Folding a left die, a left die insert, a first front die, a second front die, a third front die, an upper die of a female die in the unmanned aerial vehicle die and the right die, the right die insert, the first flexible body and the second flexible body which are paved with the fiber material on the surface in the step 2, locking the folded bodies by using a standard part to achieve the required die locking force, and completing die assembly to obtain an integral part;
and 4, step 4: monolithic heating and forming
The integral piece is only required to be placed in an oven or a press for heating and forming;
after forming, sequentially disassembling an embedded block of a female die in the unmanned aerial vehicle die, the right die insert, the left die insert, the first front die, the second front die, the third front die, the upper die and the standard part, and then taking out a formed unmanned aerial vehicle body, wherein the unmanned aerial vehicle body contains a first flexible body and a second flexible body;
and finally, taking the first flexible body out of the unmanned aerial vehicle body, and keeping the second flexible body in the unmanned aerial vehicle body to increase the rigidity of the unmanned aerial vehicle body, thereby finally obtaining the one-step curing unmanned aerial vehicle.
2. The method of claim 1, wherein the first flexible body is made of a material having a main chain formed by alternating silicon and oxygen atoms.
3. The method of claim 1, wherein the second flexible body is made of an acrylic material.
4. The method of claim 1, wherein the first flexible body is made of a material with a main chain composed of silicon and oxygen atoms alternately; the material of the second flexible body is acrylic material.
5. The method of claim 1, wherein the fiber material is a carbon fiber composite material or a glass fiber composite material.
6. The method of claim 1, wherein the first and second flexible bodies are formed of different materials.
7. The method of claim 1, wherein the first flexible body has a coefficient of expansion greater than a coefficient of expansion of the second flexible body.
8. The method of claim 1, wherein the integral piece is heated and molded in an autoclave in step 4.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811385114.7A CN109605780B (en) | 2018-11-20 | 2018-11-20 | Method for integrally forming composite material structure of unmanned aerial vehicle |
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| CN201811385114.7A CN109605780B (en) | 2018-11-20 | 2018-11-20 | Method for integrally forming composite material structure of unmanned aerial vehicle |
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| CN109605780B true CN109605780B (en) | 2021-02-19 |
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| US5122213A (en) * | 1991-01-15 | 1992-06-16 | Atlantic Research Corporation | Prestressed article and method |
| US5125993A (en) * | 1991-07-25 | 1992-06-30 | E. I. Du Pont De Nemours And Company | Method for forming and consolidating a fiber reinforced resin structure |
| TW200610640A (en) * | 2004-09-17 | 2006-04-01 | Chung Shan Inst Of Science | Method for forming composite tubes |
| US9120246B2 (en) * | 2013-03-01 | 2015-09-01 | Bell Helicopter Textron Inc. | Pressure tunable expandable mandrel for manufacturing a composite structure |
| CN106217697B (en) * | 2016-08-30 | 2018-09-14 | 山东双一科技股份有限公司 | A kind of molding die and preparation method thereof of composite material multi-rotor unmanned aerial vehicle horn |
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