CN119928300A - Carbon fiber composite UAV propeller assembly and fuselage wing rib integrated molding structure and process - Google Patents
Carbon fiber composite UAV propeller assembly and fuselage wing rib integrated molding structure and process Download PDFInfo
- Publication number
- CN119928300A CN119928300A CN202311459696.XA CN202311459696A CN119928300A CN 119928300 A CN119928300 A CN 119928300A CN 202311459696 A CN202311459696 A CN 202311459696A CN 119928300 A CN119928300 A CN 119928300A
- Authority
- CN
- China
- Prior art keywords
- carbon fiber
- rib
- fuselage
- propeller assembly
- fiber prepreg
- Prior art date
- 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.)
- Granted
Links
Classifications
-
- 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
Landscapes
- Moulding By Coating Moulds (AREA)
Abstract
The invention provides an integrated forming structure and process of a carbon fiber composite unmanned aerial vehicle propeller component and a wing rib of a machine body, which relate to the field of integrated forming of carbon fiber composite structures, and specifically comprise the following steps of (1) paving carbon fiber prepreg cloth on the propeller component and assembling the carbon fiber prepreg cloth with the wing rib of the foam sandwich machine body; the method comprises the steps of (1) paving carbon fiber prepreg cloth on a foam sandwich machine body rib structure, (3) stripping two layers of carbon fiber prepreg cloth cut at two ends of a propeller assembly and attaching the two layers of carbon fiber prepreg cloth to the paved machine body rib carbon fiber prepreg cloth, and (4) hot-press molding in a vacuum environment after coating a release agent. According to the invention, the carbon fiber prepreg cloth is paved on the surface of the propeller assembly, then the carbon fiber prepreg cloth at two ends is attached to the wing rib prepreg cloth of the aircraft body, and the integrated molding is carried out through an autoclave process, so that the connection strength between structures is greatly improved, and the connection strength of the unmanned aerial vehicle structure under various service environments is ensured.
Description
Technical Field
The invention relates to the field of integrated forming of carbon fiber composite material structures, in particular to an integrated forming structure and process of a carbon fiber composite material unmanned aerial vehicle propeller assembly and a fuselage rib.
Background
The carbon fiber composite material is widely applied in the aerospace field because of the advantages of excellent thermal shock resistance, small specific gravity, high strength, corrosion resistance, fatigue resistance, designability, integral molding and the like. In addition, unmanned aerial vehicles are often used for performing special tasks such as aerial reconnaissance, monitoring, communication, anti-diving, electronic interference and the like, so that the carbon fiber composite material has application advantages in various aspects.
At present, the connection between the carbon fiber composite material structures mostly adopts the technical methods of cementing or mechanical connection, etc. Because the gluing process not only needs to consider the compatibility of the selected adhesive and the carbon fiber composite material, but also considers the influence of various factors such as high temperature, low temperature, humidity and the like on the performance of the adhesive in a severe external environment of the unmanned aerial vehicle. The mechanical connection adopts fastening pieces for connection, on one hand, the fastening pieces can greatly influence the whole weight of the machine body, and the assembly cost and the later maintenance cost are increased. On the other hand, it is necessary to open pores in the carbon fiber composite material, causing local stress concentration, and reducing the overall strength of the structure to some extent. In order to overcome the defect of mechanical connection, an integral molding process of the propeller component and the wing rib of the machine body is invented.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide an integrated forming structure and process of a carbon fiber composite unmanned aerial vehicle propeller assembly and a fuselage rib.
According to the integrated forming process of the carbon fiber composite unmanned aerial vehicle propeller assembly and the wing rib of the fuselage, provided by the invention, the concrete steps are as follows:
s1, paving carbon fiber prepreg cloth on a propeller assembly, assembling the propeller assembly on a foam sandwich body rib, and cutting the carbon fiber prepreg between two ends of the propeller assembly and the surface of the body rib into six parts along the axis of the assembly;
S2, the cut carbon fiber prepreg cloth is paved on a wing rib structure of the foam sandwich fuselage twice, a certain margin is reserved at the contact part of the carbon fiber prepreg cloth and the propeller assembly, and a plurality of carbon fiber prepreg cloths are attached to the propeller assembly;
S3, stripping and attaching the carbon fiber prepregs cut at the two ends of the propeller assembly in the S1 to the carbon fiber prepreg cloth of the wing rib of the fuselage paved in the S3;
S4, coating a release agent on the surface of a workbench and the surface of the die for placing the die;
S5, after the die and the structure are combined on the workbench, placing an airfelt and a separation membrane on the workbench, and sealing by using a sealing adhesive tape after vacuum bagging.
And S6, vacuumizing the vacuum bag to ensure that no air leakage exists, and then placing the vacuum bag into an autoclave.
In the step S2, the cut carbon fiber prepreg cloth is laid along the inner surface of the rib of the foam sandwich fuselage, and has round holes, square holes and irregular holes, the carbon fiber prepreg cloth passes through the holes and is then attached to the outer surface of the rib of the foam sandwich fuselage to just wrap the inner and outer surfaces of the rib of the fuselage, then the second layer of carbon fiber prepreg is laid on the outer surface of the rib structure of the fuselage, which is already attached with one layer of prepreg, and the second layer of carbon fiber prepreg is laid by the way of laying the inner layer, so that the whole rib structure of the foam sandwich fuselage is wrapped in the two layers of carbon fiber prepregs.
Preferably, in the above step S6, the autoclave is warmed from room temperature to 123℃and kept at a pressure of 0.5MPa for 2 hours.
Preferably, the autoclave has a temperature rise rate of 1℃per minute.
Preferably, in the above step S6, when the temperature is reduced to 60 ℃, the autoclave pressure is adjusted to 0MPa.
Preferably, the autoclave is cooled at a rate of 1℃per minute.
A carbon fiber composite unmanned aerial vehicle propeller component and fuselage rib integrated into one piece structure adopts carbon fiber composite unmanned aerial vehicle propeller component and fuselage rib integrated into one piece technology.
Preferably, the device comprises a propeller assembly, a body rib and a forming die, wherein the body rib is connected to the propeller assembly, and the forming die is respectively connected with the body rib and the propeller assembly.
Preferably, the wing rib part of the fuselage is of a carbon fiber prepreg wrapped foam sandwich structure, and the propeller component is of an all-carbon fiber composite round tube formed by a winding process.
Preferably, the forming die is a slider combination of a involutory integral structure.
Compared with the prior art, the invention has the following beneficial effects:
According to the invention, the carbon fiber prepreg cloth is paved on the surface of the propeller assembly, then the carbon fiber prepreg cloth at two ends is attached to the wing rib prepreg cloth of the aircraft body, and the integrated molding is carried out through an autoclave process, so that the connection strength between structures is greatly improved, and the connection strength of the unmanned aerial vehicle structure under various service environments is ensured.
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a schematic diagram of the overall structure of the present invention;
FIG. 2 (a) is a die isometric view;
FIG. 2 (b) is a front view of the mold;
FIG. 2 (c) is a positive three-axis view of the mold;
FIG. 2 (d) is a right side view of the mold;
FIG. 2 (e) is a top view of the mold;
fig. 2 (f) is a left side view of the mold.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present invention.
Example 1
The invention provides an integrated forming process of a carbon fiber composite unmanned aerial vehicle propeller assembly and a fuselage rib, which comprises the following specific steps:
s1, paving two layers of carbon fiber prepreg on the surfaces of a foam core layer body rib and a full carbon fiber propeller assembly, wherein the carbon fiber prepreg is cut into carbon fiber prepreg cloth capable of completely wrapping the body and the propeller assembly according to the shape and the size of the body rib and the propeller assembly;
s2, firstly laying the carbon fiber prepreg cloth cut in the S1 on a propeller assembly, then assembling the carbon fiber prepreg cloth on a foam sandwich machine body rib, and cutting the carbon fiber prepreg between two ends of the propeller assembly and the surface of the machine body rib into six parts along the axis of the assembly so as to be attached to the machine body carbon fiber prepreg later;
S3, paving the carbon fiber prepreg cloth cut in the S1 on the wing rib structure of the foam sandwich body twice, paving the cut carbon fiber prepreg cloth along the inner surface of the foam sandwich body and having round holes, square holes and irregular holes, enabling the carbon fiber prepreg cloth to pass through the holes and then be attached to the outer surface of the foam sandwich body so as to just wrap the inner surface and the outer surface of the structure;
S4, in the step (3), carbon fiber prepreg cloth with a certain margin is reserved at the contact part with the propeller assembly, and the carbon fiber prepreg cloth with a plurality of parts is attached to the surface of the propeller assembly, so that the connection between the wing ribs of the machine body and the propeller assembly is more stable after the subsequent solidification is completed;
s5, stripping two layers of carbon fiber prepreg cloth cut at two ends of the propeller assembly in the step (2) and attaching the two layers of carbon fiber prepreg cloth to the wing rib carbon fiber prepreg cloth of the machine body laid in the step (3);
S6, spreading carbon fiber prepreg cloth, and then coating the carbon fiber prepreg cloth on a workbench for placing a die and the surface of the die for three times by using a stripper;
S7, the mould and the structure are combined on a workbench, an airfelt and a separation membrane are placed on the mould and the structure, a vacuum bag is made and the mould and the structure are sealed by a sealing adhesive tape;
s8, vacuumizing the vacuum bag to ensure no air leakage, putting the vacuum bag into an autoclave, increasing the temperature of the autoclave from room temperature to 123 ℃ at 1 ℃ per minute, keeping the temperature for 2 hours (the temperature increasing system is determined according to different prepreg curing performances), wherein the pressure is 0.5MPa, the speed in the cooling process is 1 ℃ per minute, and reducing the pressure to 0MPa when the temperature is reduced to 60 ℃.
Example 2
The invention provides an integrated forming structure of a carbon fiber composite unmanned aerial vehicle propeller component and a wing rib of a wing body, which is shown in fig. 1-2, and adopts the integrated forming process of the carbon fiber composite unmanned aerial vehicle propeller component and the wing rib of the wing body in embodiment 1. The device comprises a propeller assembly, a body wing rib and a forming die, wherein the body wing rib is connected to the propeller assembly, and the forming die is respectively connected with the body wing rib and the propeller assembly. The wing rib part of the aircraft body is of a foam sandwich structure wrapped by carbon fiber prepreg, the propeller component is a round tube of all-carbon fiber composite material formed by a winding process, and the forming die is a slider combination of a involutory integral structure.
In the description of the present application, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present application.
The foregoing describes specific embodiments of the present application. It is to be understood that the application is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the application. The embodiments of the application and the features of the embodiments may be combined with each other arbitrarily without conflict.
Claims (10)
1. A carbon fiber composite unmanned aerial vehicle propeller component and fuselage rib integrated into one piece technology, its characteristic is that, the concrete step is as follows:
s1, paving carbon fiber prepreg cloth on a propeller assembly, assembling the propeller assembly on a foam sandwich body rib, and cutting the carbon fiber prepreg between two ends of the propeller assembly and the surface of the body rib into six parts along the axis of the assembly;
S2, the cut carbon fiber prepreg cloth is paved on a wing rib structure of the foam sandwich fuselage twice, a certain margin is reserved at the contact part of the carbon fiber prepreg cloth and the propeller assembly, and a plurality of carbon fiber prepreg cloths are attached to the propeller assembly;
S3, stripping and attaching the carbon fiber prepregs cut at the two ends of the propeller assembly in the S1 to the carbon fiber prepreg cloth of the wing rib of the fuselage paved in the S3;
S4, coating a release agent on the surface of a workbench and the surface of the die for placing the die;
S5, after the die and the structure are combined on the workbench, placing an airfelt and a separation membrane on the workbench, and sealing by using a sealing adhesive tape after vacuum bagging.
And S6, vacuumizing the vacuum bag to ensure that no air leakage exists, and then placing the vacuum bag into an autoclave.
2. The unmanned aerial vehicle propeller assembly and fuselage rib integrated molding process of claim 1, wherein in the step S2, firstly, the cut carbon fiber prepreg cloth is paved along the inner surface of the foam sandwich fuselage rib, and is provided with round holes, square holes and irregular holes, the carbon fiber prepreg cloth passes through the holes and is attached to the outer surface of the foam sandwich fuselage rib to just wrap the inner surface and the outer surface of the fuselage rib, then, a second layer of carbon fiber prepreg is firstly paved on the outer surface of the fuselage rib structure which is already attached with one layer of prepreg, and a second layer is paved by paving an inner layer, so that the whole foam sandwich fuselage rib structure is wrapped in two layers of carbon fiber prepregs.
3. The process for integrally forming the carbon fiber composite unmanned aerial vehicle propeller assembly and the wing ribs of the fuselage according to claim 1, wherein in the step S6, the autoclave is heated from room temperature to 123 ℃ and kept at a pressure of 0.5MPa for 2 hours.
4. The carbon fiber composite unmanned aerial vehicle propeller assembly and fuselage rib integrated molding process of claim 3, wherein the autoclave has a heating rate of 1 ℃ per minute.
5. The process for integrally forming a carbon fiber composite unmanned aerial vehicle propeller assembly and a fuselage rib according to claim 1, wherein in the step S6, when the temperature is reduced to 60 ℃, the autoclave pressure is adjusted to 0MPa.
6. The carbon fiber composite unmanned aerial vehicle propeller assembly and fuselage rib integrated molding process of claim 5, wherein the autoclave has a cooling rate of 1 ℃ per minute.
7. An integrated structure of a carbon fiber composite unmanned aerial vehicle propeller assembly and a wing rib of a fuselage, which is characterized in that the integrated process of the carbon fiber composite unmanned aerial vehicle propeller assembly and the wing rib of the fuselage is adopted.
8. The carbon fiber composite unmanned aerial vehicle screw assembly and fuselage rib integrated into one piece structure of claim 7, comprising screw assembly, fuselage rib and forming die, the fuselage rib connect in on the screw assembly, forming die connects respectively the fuselage rib with the screw assembly.
9. The carbon fiber composite unmanned aerial vehicle screw assembly and fuselage rib integrated into one piece structure of claim 8, wherein the fuselage rib part is a carbon fiber prepreg wrapped foam sandwich structure, and the screw assembly is an all-carbon fiber composite round tube formed by a winding process.
10. The carbon fiber composite unmanned aerial vehicle propeller assembly and fuselage rib integrally formed structure of claim 8, wherein the forming die is a slider assembly of a closed overall structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311459696.XA CN119928300B (en) | 2023-11-03 | 2023-11-03 | Carbon fiber composite UAV propeller assembly and fuselage wing rib integrated molding structure and process |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311459696.XA CN119928300B (en) | 2023-11-03 | 2023-11-03 | Carbon fiber composite UAV propeller assembly and fuselage wing rib integrated molding structure and process |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN119928300A true CN119928300A (en) | 2025-05-06 |
| CN119928300B CN119928300B (en) | 2025-11-21 |
Family
ID=95540123
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311459696.XA Active CN119928300B (en) | 2023-11-03 | 2023-11-03 | Carbon fiber composite UAV propeller assembly and fuselage wing rib integrated molding structure and process |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN119928300B (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104192292A (en) * | 2014-09-17 | 2014-12-10 | 中航通飞华南飞机工业有限公司 | Composite integral co-curing aircraft body and processing method |
| US20160341178A1 (en) * | 2014-01-31 | 2016-11-24 | Lm Wp Patent Holding A/S | Wind turbine blade with improved fibre transition |
| CN107745531A (en) * | 2017-09-19 | 2018-03-02 | 衡阳泰豪通信车辆有限公司 | A kind of bridging method of carbon fiber pipe |
| CN110614781A (en) * | 2019-08-21 | 2019-12-27 | 湖南欧亚碳纤维复合材料有限公司 | Helicopter body and other integrated forming process |
| JP2020090110A (en) * | 2018-12-03 | 2020-06-11 | 川崎重工業株式会社 | COMPOSITE MATERIAL AIRCRAFT PART AND METHOD OF MANUFACTURING THE SAME |
| CN213832083U (en) * | 2020-10-19 | 2021-07-30 | 北京蓝科盈晟航空科技有限公司 | Co-curing composite material unmanned aerial vehicle fuselage |
| WO2022131166A1 (en) * | 2020-12-17 | 2022-06-23 | 三菱ケミカル株式会社 | Connection part, method for manufacturing sheet molding compound, and method |
-
2023
- 2023-11-03 CN CN202311459696.XA patent/CN119928300B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20160341178A1 (en) * | 2014-01-31 | 2016-11-24 | Lm Wp Patent Holding A/S | Wind turbine blade with improved fibre transition |
| CN104192292A (en) * | 2014-09-17 | 2014-12-10 | 中航通飞华南飞机工业有限公司 | Composite integral co-curing aircraft body and processing method |
| CN107745531A (en) * | 2017-09-19 | 2018-03-02 | 衡阳泰豪通信车辆有限公司 | A kind of bridging method of carbon fiber pipe |
| JP2020090110A (en) * | 2018-12-03 | 2020-06-11 | 川崎重工業株式会社 | COMPOSITE MATERIAL AIRCRAFT PART AND METHOD OF MANUFACTURING THE SAME |
| CN110614781A (en) * | 2019-08-21 | 2019-12-27 | 湖南欧亚碳纤维复合材料有限公司 | Helicopter body and other integrated forming process |
| CN213832083U (en) * | 2020-10-19 | 2021-07-30 | 北京蓝科盈晟航空科技有限公司 | Co-curing composite material unmanned aerial vehicle fuselage |
| WO2022131166A1 (en) * | 2020-12-17 | 2022-06-23 | 三菱ケミカル株式会社 | Connection part, method for manufacturing sheet molding compound, and method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN119928300B (en) | 2025-11-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105904740B (en) | A kind of integral manufacturing method of composite material light continuous fiber grid | |
| CA2862394C (en) | One-piece composite bifurcated winglet | |
| US10479032B2 (en) | Method of fabricating a vacuum barrier system | |
| EP2703429B1 (en) | Method and system to reduce porosity in composite structures | |
| CN109016562B (en) | Preparation method of wingtip winglet | |
| US11712871B2 (en) | Large cell carbon core sandwich panel and method of manufacturing same | |
| CN103273662B (en) | The preparation method of low-thermal-expansion carbon fiber enhancement resin base composite material mould | |
| US20160167315A1 (en) | Bagging process and mandrel for fabrication of elongated composite structure | |
| CN111186143B (en) | Integrated forming process for composite nose cone of unmanned aerial vehicle electric cabin | |
| CN106207029A (en) | A kind of batteries of electric automobile pallet and manufacture method thereof | |
| CN107738457A (en) | A kind of integrated forming technique of unmanned aerial vehicle body | |
| CN106273547A (en) | One has cabin cover and Ω stringer deep camber unmanned plane wallboard manufacturing process | |
| CN110193956A (en) | A kind of small drone composite material vertical tail moulding technique | |
| CN113619155A (en) | Integral co-curing forming die and method for unmanned aerial vehicle body and rotor wing rod | |
| US20150210019A1 (en) | Methods for combining components of varying stages of cure | |
| CN119928300B (en) | Carbon fiber composite UAV propeller assembly and fuselage wing rib integrated molding structure and process | |
| US10086534B2 (en) | Multifunctional mandrel end cap and method | |
| CN115570808B (en) | Propeller cap forming method of propeller composite material and propeller cap | |
| CN111497275B (en) | Female die forming process method of composite material rear pressure partition frame | |
| CN210618478U (en) | A throwing type unmanned aerial vehicle and its protective tube | |
| CN111497284A (en) | Co-curing molding method of spherical frame of airplane | |
| CN114919205A (en) | Preparation method of unmanned aerial vehicle composite material body structure | |
| CN207594367U (en) | A kind of mold for preparing glass fibre bend pipe | |
| CN107839254B (en) | Preparation method and mold for glass fiber bent pipe | |
| CN110562462B (en) | Throwing type unmanned aerial vehicle and protection barrel thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |