CN114571663A - Processing technology of rotary wing panel of gyroplane - Google Patents
Processing technology of rotary wing panel of gyroplane Download PDFInfo
- Publication number
- CN114571663A CN114571663A CN202210157196.XA CN202210157196A CN114571663A CN 114571663 A CN114571663 A CN 114571663A CN 202210157196 A CN202210157196 A CN 202210157196A CN 114571663 A CN114571663 A CN 114571663A
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- China
- Prior art keywords
- skin
- cavity
- girder
- lower skin
- upper skin
- 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.)
- Pending
Links
- 238000005516 engineering process Methods 0.000 title claims abstract description 6
- 238000004519 manufacturing process Methods 0.000 claims abstract description 27
- 238000000034 method Methods 0.000 claims abstract description 19
- 229920000271 Kevlar® Polymers 0.000 claims abstract description 13
- 238000004026 adhesive bonding Methods 0.000 claims abstract description 13
- 239000004761 kevlar Substances 0.000 claims abstract description 13
- 238000002347 injection Methods 0.000 claims abstract description 12
- 239000007924 injection Substances 0.000 claims abstract description 12
- 239000011248 coating agent Substances 0.000 claims abstract description 9
- 238000000576 coating method Methods 0.000 claims abstract description 9
- 239000004033 plastic Substances 0.000 claims abstract description 8
- 229920003023 plastic Polymers 0.000 claims abstract description 8
- 239000006260 foam Substances 0.000 claims abstract description 7
- 239000000463 material Substances 0.000 claims abstract description 7
- 229910000838 Al alloy Inorganic materials 0.000 claims abstract description 4
- 238000001125 extrusion Methods 0.000 claims abstract description 4
- 239000000945 filler Substances 0.000 claims description 17
- 239000003365 glass fiber Substances 0.000 claims description 5
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 3
- 239000004917 carbon fiber Substances 0.000 claims description 3
- 238000005520 cutting process Methods 0.000 claims description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical group C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 2
- 239000000243 solution Substances 0.000 description 4
- 238000001746 injection moulding Methods 0.000 description 3
- 230000005484 gravity Effects 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- 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
- B29C45/00—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor
- B29C45/14—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles
- B29C45/14008—Inserting articles into the mould
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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
- B29C45/00—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor
- B29C45/14—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles
- B29C45/14311—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles using means for bonding the coating to the articles
-
- 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
Abstract
The invention provides a processing technology of a rotary wing panel of a rotorcraft, which comprises the following steps: manufacturing a crossbeam through an aluminum alloy extrusion molding process; respectively placing an upper skin and a lower skin on the upper surface and the lower surface of an inner cavity of an injection mold; inserting a girder as an embedded part between an upper skin and a lower skin, and gluing the joint of the upper skin and the lower skin; injecting foam plastic into a cavity between the upper skin and the lower skin from the end faces of the upper skin and the lower skin through an injection mold; carrying out skin treatment on the end parts of the upper skin and the lower skin, wherein the material used for the skins is the same as the material used for manufacturing the upper skin and the lower skin; and then integrally coating the upper skin and the lower skin through the Kevlar, and finally coating a layer of surface skin on the surface of the Kevlar. The invention solves the problem of low production efficiency in the prior art and has the effect of improving the production efficiency of the rotor blade.
Description
Technical Field
The invention relates to the technical field of gyroplanes, in particular to a processing technology of a gyroplane rotor blade.
Background
The rotor is the main lift component of rotor aircrafts such as helicopters, gyroplanes and the like, and the rotor consists of a hub and a plurality of blades, and the blades are rotor blades.
The existing rotor wing panel, as disclosed in chinese patent CN104002966B, is a rotor blade configuration design for suppressing rotation flutter of a tilt rotor aircraft, which includes a blade girder, a skin and a filler core, wherein the girder and the skin, the filler and the skin, and the girder and the filler are connected by gluing; in the aspect of manufacturing, the three parts are produced independently and then assembled and glued, so that the quality of the parts can be guaranteed, but the production process is complicated, and the production efficiency is low.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a processing technology of a rotary wing panel of a rotorcraft, which solves the problem of low production efficiency in the prior art.
According to an embodiment of the invention, a process for machining a rotorcraft rotor blade includes the steps of:
s1, manufacturing the crossbeam through an aluminum alloy extrusion molding process, and cutting a section according to design requirements;
s2, respectively manufacturing an upper skin and a lower skin through a mould, and respectively placing the upper skin and the lower skin on the upper surface and the lower surface of an inner cavity of an injection mould;
s3, inserting the girder as an embedded part between an upper skin and a lower skin, gluing the surface of the girder, enclosing the upper skin and the lower skin into a cavity with a water-drop-shaped cross section, and gluing the joint of the upper skin and the lower skin;
s4, injecting foam plastics into the cavity between the upper skin and the lower skin from the end faces of the upper skin and the lower skin through an injection mold, and forming a filling core after the foam plastics are molded;
s5, performing skin treatment on the ends of the upper skin and the lower skin, wherein the materials used for the skins are the same as those used for manufacturing the upper skin and the lower skin;
s6, integrally coating the upper skin and the lower skin through the Kevlar, and finally coating a layer of skin on the surface of the Kevlar.
Preferably, the girder is arranged at the thick end of the water drop-shaped cavity, and the outer surface of the girder is attached to the inner surfaces of the upper skin and the lower skin.
Preferably, a first cavity and a second cavity are formed in the girder along the axial direction of the girder, the first cavity is close to the thicker end of the cavity, and the end part of the first cavity far away from the second cavity is arranged into an arc shape.
Preferably, a notch is formed in the end part of the girder, which is far away from the thicker end of the cavity, and the bottom surface of the notch is wider than the top opening of the notch.
Preferably, the upper skin and the lower skin are both made of glass fiber, and the skin coated on the surface of the Kevlar is carbon fiber.
Compared with the prior art, the invention has the following beneficial effects:
processing the upper skin and the lower skin through a mold, so that the edges of the upper skin and the lower skin except for one end used for injection molding can be completely jointed, respectively installing the manufactured upper skin and the manufactured lower skin in an upper template and a lower template of the injection mold, placing a girder as an embedded part in a cavity between the upper skin and the lower skin, gluing the edges of the upper skin and the lower skin before mold assembly, then performing mold assembly and injection molding, and finally performing skin covering on one ends of the upper skin and the lower skin used for injection molding; the whole processing process omits the process of independently manufacturing and gluing the filler, reduces the production procedures and improves the production efficiency.
Drawings
Fig. 1 is a schematic structural diagram of an embodiment of the present invention.
Fig. 2 is a cross-sectional view of an embodiment of the present invention.
In the drawings, wherein: 10. a girder; 11. a first cavity; 12. a second cavity; 13. a notch; 20. filling a core; 21. a strip-shaped bulge; 30. covering the skin; 40. and a lower skin.
Detailed Description
The technical solution of the present invention is further explained with reference to the drawings and the embodiments.
As shown in fig. 1-2, in order to improve the production efficiency of the rotor blade, an embodiment of the present invention provides a processing technique for a rotor blade of a rotorcraft, including the following steps:
s1, manufacturing the girder 10 through an aluminum alloy extrusion molding process, and cutting a section according to design requirements;
s2, respectively manufacturing the upper skin 30 and the lower skin 40 through a mould, and respectively placing the upper skin 30 and the lower skin 40 on the upper surface and the lower surface of an inner cavity of an injection mould;
s3, inserting the girder 10 as an embedded part between the upper skin 30 and the lower skin 40, gluing the surface of the girder 10, enclosing the upper skin 30 and the lower skin 40 to form a cavity with a water-drop-shaped cross section, and gluing the joint of the upper skin 30 and the lower skin 40;
s4, injecting foam plastics into the cavity between the upper skin 30 and the lower skin 40 from the end faces of the upper skin 30 and the lower skin 40 through an injection mold, and forming the filler 20 after the foam plastics are molded;
s5, performing skin treatment on the ends of the upper skin 30 and the lower skin 40, wherein the materials of the skins are the same as those used for manufacturing the upper skin 30 and the lower skin 40;
s6, integrally coating the upper skin 30 and the lower skin 40 through the Kevlar, and finally coating a layer of skin on the surface of the Kevlar.
The method comprises the steps that an upper skin 30 and a lower skin 40 are shaped through a mold, and after the upper skin 30 and the lower skin 40 are stabilized, the upper skin 30 and the lower skin 40 are respectively transferred to an upper module and a lower module of an injection mold; the die assembly process of the upper die set and the lower die set comprises the steps that one die set horizontally moves relative to the other die set, the girder 10 is pre-embedded in a skin before die assembly, surface gluing is carried out on the girder 10, and the outer surface of the girder 10 is conveniently glued with the inner bottom surfaces of the upper skin 30 and the lower skin 40;
before die assembly, gluing the edge of the upper skin 30 or the lower skin 40, reserving a slot for a girder 10 to pass through in the injection mold, limiting the girder 10 by the slot, enabling one end of the girder 10 to pass through the end, which is not connected with the upper skin 30 and the lower skin 40, of the upper skin 30 and the lower skin 40, and injecting foamed plastic into the cavity through a flow channel of the injection mold while realizing gluing between the upper skin 30 and the lower skin 40;
after the core filling 20 is formed, since the girder 10 penetrates through the unconnected end of the upper skin 30 and the lower skin 40, the connection structure can be installed at the end of the girder 10, and the whole rotor blade is installed on the hub;
and finally, performing Kevlar coating on the upper skin 30 and the lower skin 40, covering the end part of the filler 20, connecting the unconnected ends of the upper skin 30 and the lower skin 40, finishing the processing of the whole rotor wing piece, omitting the process of separately manufacturing and cementing the filler 20 in the whole processing process, and improving the processing efficiency of the rotor wing piece.
As shown in fig. 2, in order to facilitate stable installation of the girder 10, the girder 10 is disposed at a thick end of the cavity in a drop shape, and an outer surface of the girder 10 is attached to inner surfaces of the upper and lower skins 30 and 40.
In the surface design of the girder 10, the girder 10 is divided into two mirror symmetry side surfaces, the two side surfaces are respectively attached to the inner bottom surfaces of the upper skin 30 and the lower skin 40, in the machining process of the filler 20, the surface of the girder 10 is coated with glue, in the die assembly process of the filler 20, the outer surface of the girder 10 is directly attached to the inner bottom surfaces of the upper skin 30 and the lower skin 40, the girder 10 is effectively fixed, and the filler 20 is distributed on one side (namely the thin end of the cavity) of the girder 10, so that the design of the rotating direction gravity center of the rotating wing piece is facilitated.
As shown in fig. 2, in order to provide stability of the rotor blade, a first cavity 11 and a second cavity 12 are formed in the girder 10 along an axial direction of the girder 10, the first cavity 11 is close to a thicker end of the cavity, and an end of the first cavity 11 far from the second cavity 12 is configured in an arc shape.
By arranging the first cavity 11 and the second cavity 12, the rotating direction gravity center of the rotor blade is controlled to be positioned on the width quartering point of the rotor blade close to the thicker end, and meanwhile, the material cost for manufacturing the girder 10 can be saved; the end part of the first cavity 11 is set to be arc-shaped, so that the stress stability of the first cavity 11 is enhanced.
As shown in fig. 1-2, in order to stabilize the connection between the core filler 20 and the girder 10, a notch 13 is formed at an end of the girder 10 away from a thicker end of the cavity, and a bottom surface of the notch 13 is wider than a top opening of the notch 13.
Through the opening narrowly, the wide notch 13 in bottom is connected with the filler 20, in the course of processing the filler 20, the filler 20 will be full of the notch 13, and form the bar-shaped protrusion 21 in the notch 13, with the cooperation of bar-shaped protrusion 21 and notch 13, carry out the girder 10 and be connected with the filler 20, improve the stability that the filler 20 is connected with the girder 10.
In order to improve the strength of the skin, the upper skin 30 and the lower skin 40 are made of glass fiber, and the skin coated on the kevlar surface is made of carbon fiber. The glass fiber is used as the base material of the skin, and the Kevlar is laid on the surface of the glass fiber, so that the strength of the rotor wing piece is improved, and the rotor wing piece is prevented from deforming.
Finally, the above embodiments are only for illustrating the technical solutions of the present invention and not for limiting, although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that modifications or equivalent substitutions may be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all of them should be covered in the claims of the present invention.
Claims (5)
1. A processing technology of a rotary wing panel of a rotorcraft is characterized in that: the method comprises the following steps:
s1, manufacturing the crossbeam (10) through an aluminum alloy extrusion molding process, and cutting out a section according to design requirements;
s2, respectively manufacturing an upper skin (30) and a lower skin (40) through a mould, and respectively placing the upper skin (30) and the lower skin (40) on the upper surface and the lower surface of an inner cavity of an injection mould;
s3, inserting the girder (10) between the upper skin (30) and the lower skin (40) as an embedded part, gluing the surface of the girder (10), enclosing the upper skin (30) and the lower skin (40) into a cavity with a water-drop-shaped cross section, and gluing the joint of the upper skin (30) and the lower skin (40);
s4, injecting foam plastics into the cavity between the upper skin (30) and the lower skin (40) from the end faces of the upper skin (30) and the lower skin (40) through an injection mold, and forming the filler (20) after the foam plastics are molded;
s5, performing skin treatment on the ends of the upper skin (30) and the lower skin (40), wherein the material of the skins is the same as that used for manufacturing the upper skin (30) and the lower skin (40);
s6, integrally coating the upper skin (30) and the lower skin (40) through a Kevlar, and finally coating a layer of skin on the surface of the Kevlar.
2. A process for manufacturing a rotorcraft rotor blade according to claim 1, wherein: the girder (10) is arranged at the thick end of the water drop-shaped cavity, and the outer surface of the girder (10) is attached to the inner surfaces of the upper skin (30) and the lower skin (40).
3. A process for manufacturing a rotorcraft rotor blade according to claim 2, wherein: a first cavity (11) and a second cavity (12) are formed in the girder (10) along the axial direction of the girder (10), the first cavity (11) is close to the thick end of the cavity, and the end part, far away from the second cavity (12), of the first cavity (11) is arranged into an arc shape.
4. A process for manufacturing a rotorcraft rotor blade according to claim 3, wherein: the end part of the girder (10) far away from the thicker end of the cavity is provided with a notch (13), and the bottom surface of the notch (13) is wider than the top opening of the notch (13).
5. A process for manufacturing a rotorcraft rotor blade according to claim 1, wherein: the upper skin (30) and the lower skin (40) are both made of glass fiber, and the skin coated on the surface of the Kevlar is carbon fiber.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210157196.XA CN114571663A (en) | 2022-02-21 | 2022-02-21 | Processing technology of rotary wing panel of gyroplane |
| CN202311797231.5A CN117799110A (en) | 2022-02-21 | 2022-02-21 | Processing technology of gyroplane rotor blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210157196.XA CN114571663A (en) | 2022-02-21 | 2022-02-21 | Processing technology of rotary wing panel of gyroplane |
Related Child Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311797231.5A Division CN117799110A (en) | 2022-02-21 | 2022-02-21 | Processing technology of gyroplane rotor blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114571663A true CN114571663A (en) | 2022-06-03 |
Family
ID=81774278
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311797231.5A Pending CN117799110A (en) | 2022-02-21 | 2022-02-21 | Processing technology of gyroplane rotor blade |
| CN202210157196.XA Pending CN114571663A (en) | 2022-02-21 | 2022-02-21 | Processing technology of rotary wing panel of gyroplane |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311797231.5A Pending CN117799110A (en) | 2022-02-21 | 2022-02-21 | Processing technology of gyroplane rotor blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (2) | CN117799110A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB637827A (en) * | 1946-10-31 | 1950-05-24 | Autogiro Co Of America | Improvements in sustaining rotor blades for aircraft |
| GB818403A (en) * | 1955-10-31 | 1959-08-19 | Aerotecnica S A | Rotor blades for rotary wing aircraft |
| GB1361174A (en) * | 1972-02-14 | 1974-07-24 | United Aircraft Corp | Helicopter rotor blade and method of fabricating same |
| JP2012071805A (en) * | 2010-09-30 | 2012-04-12 | Society Of Japanese Aerospace Co Inc | Aerofoil structure using fiber reinforced composite material, and manufacturing method therefor |
| CN204955296U (en) * | 2015-09-29 | 2016-01-13 | 深圳聚科精密机电有限公司 | Casting mould of unmanned aerial vehicle rotor |
| CN109228375A (en) * | 2018-11-01 | 2019-01-18 | 成都纵横大鹏无人机科技有限公司 | A kind of covering, covering prepare mold, covering forming method |
| CN112238551A (en) * | 2020-09-27 | 2021-01-19 | 航天特种材料及工艺技术研究所 | Multi-part integrated forming assembly die and forming assembly method for composite wing |
-
2022
- 2022-02-21 CN CN202311797231.5A patent/CN117799110A/en active Pending
- 2022-02-21 CN CN202210157196.XA patent/CN114571663A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB637827A (en) * | 1946-10-31 | 1950-05-24 | Autogiro Co Of America | Improvements in sustaining rotor blades for aircraft |
| GB818403A (en) * | 1955-10-31 | 1959-08-19 | Aerotecnica S A | Rotor blades for rotary wing aircraft |
| GB1361174A (en) * | 1972-02-14 | 1974-07-24 | United Aircraft Corp | Helicopter rotor blade and method of fabricating same |
| JP2012071805A (en) * | 2010-09-30 | 2012-04-12 | Society Of Japanese Aerospace Co Inc | Aerofoil structure using fiber reinforced composite material, and manufacturing method therefor |
| CN204955296U (en) * | 2015-09-29 | 2016-01-13 | 深圳聚科精密机电有限公司 | Casting mould of unmanned aerial vehicle rotor |
| CN109228375A (en) * | 2018-11-01 | 2019-01-18 | 成都纵横大鹏无人机科技有限公司 | A kind of covering, covering prepare mold, covering forming method |
| CN112238551A (en) * | 2020-09-27 | 2021-01-19 | 航天特种材料及工艺技术研究所 | Multi-part integrated forming assembly die and forming assembly method for composite wing |
Non-Patent Citations (1)
| Title |
|---|
| TERRY RICHARDSON: "《复合材料设计指南》", 武汉：武汉工业大学出版社, pages: 98 * |
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| Publication number | Publication date |
|---|---|
| CN117799110A (en) | 2024-04-02 |
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