CN117799110A - Processing technology of gyroplane rotor blade - Google Patents
Processing technology of gyroplane rotor blade Download PDFInfo
- Publication number
- CN117799110A CN117799110A CN202311797231.5A CN202311797231A CN117799110A CN 117799110 A CN117799110 A CN 117799110A CN 202311797231 A CN202311797231 A CN 202311797231A CN 117799110 A CN117799110 A CN 117799110A
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- skin
- girder
- cavity
- upper skin
- lower skin
- Prior art date
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- Pending
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- 238000005516 engineering process Methods 0.000 title claims abstract description 10
- 210000003491 skin Anatomy 0.000 claims abstract description 168
- 238000004519 manufacturing process Methods 0.000 claims abstract description 29
- 238000000034 method Methods 0.000 claims abstract description 26
- 238000002347 injection Methods 0.000 claims abstract description 16
- 239000007924 injection Substances 0.000 claims abstract description 16
- 238000004026 adhesive bonding Methods 0.000 claims abstract description 13
- 239000000463 material Substances 0.000 claims abstract description 10
- 239000006260 foam Substances 0.000 claims abstract description 8
- 239000004033 plastic Substances 0.000 claims abstract description 8
- 229910000838 Al alloy Inorganic materials 0.000 claims abstract description 4
- 238000001125 extrusion Methods 0.000 claims abstract description 4
- 210000002615 epidermis Anatomy 0.000 claims abstract description 3
- 239000011248 coating agent Substances 0.000 claims description 6
- 238000000576 coating method Methods 0.000 claims description 6
- 239000003365 glass fiber Substances 0.000 claims description 5
- 230000005484 gravity Effects 0.000 claims description 5
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 5
- 229920000271 Kevlar® Polymers 0.000 claims description 4
- 239000004761 kevlar Substances 0.000 claims description 4
- 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
- 239000002002 slurry Substances 0.000 claims 1
- 239000000945 filler Substances 0.000 abstract description 4
- 238000001746 injection moulding Methods 0.000 description 3
- 239000000243 solution Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 230000002401 inhibitory effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical group C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Mechanical Engineering (AREA)
- Injection Moulding Of Plastics Or The Like (AREA)
- Laminated Bodies (AREA)
Abstract
The invention discloses a processing technology of a gyroplane rotor blade, which comprises the following steps: manufacturing a girder 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; the girder is inserted between the upper skin and the lower skin as an embedded part, and the joint of the upper skin and the lower skin is glued; 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; performing skin treatment on the end parts of the upper skin and the lower skin, wherein the material used by the skins is the same as the material used for manufacturing the upper skin and the lower skin; and then the upper skin and the lower skin are integrally coated by the Kjeldahl, and finally a layer of epidermis is coated on the surface of the Kjeldahl. The invention omits the process of independently manufacturing and gluing the filler in the whole processing process, reduces the production procedures, improves the production efficiency and solves the problem of lower production efficiency of the rotor blade in the prior art.
Description
The application is a divisional application of a patent application named as processing technology of rotary wing panel of gyroplane, and the application date of the original application is 2022, 02 and 21, and the application number is 202210157196.X.
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 a main lifting component of a helicopter, a rotorcraft and other rotorcraft, the rotor consists of a hub and a plurality of blades, and the blades are rotor blades.
The existing rotor blade is designed into a rotor blade configuration for inhibiting the rotary flutter of a tiltrotor aircraft, as disclosed in Chinese patent CN104002966B, and comprises a blade girder, a skin and a filling core, wherein the girder is connected with the skin, a filler is connected with the skin and the girder is connected with the filler in a cementing mode; in manufacturing, 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 complex, 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 rotorcraft rotor blade, which solves the problems of complex production procedures and low production efficiency in the prior art.
In order to solve the technical problems, the invention adopts the following technical scheme:
the invention relates to a processing technology of a gyroplane rotor blade, which comprises the following steps:
s1, manufacturing a girder 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 die, and respectively placing the upper skin and the lower skin in an upper die set and a lower die set of an injection die after the upper skin and the lower skin are stable, wherein the die assembly process of the upper die set and the lower die set is that one die set moves horizontally relative to the other die set;
s3, inserting the girder as an embedded part between an upper skin and a lower skin, and performing gluing treatment on the surface of the girder so as to glue the outer surface of the girder with the inner bottom surfaces of the upper skin and the lower skin, wherein the upper skin and the lower skin enclose a cavity with a water drop-shaped cross section, gluing the edge of the upper skin or the lower skin, reserving a slot for the girder to pass through in an injection mold, limiting the girder through the slot, penetrating one end of the girder out of the unconnected end of the upper skin and the lower skin, forming a notch at the end of the girder, far away from the thicker end of the cavity, wherein the bottom surface of the notch is wider than the top opening of the notch, and gluing the joint of the upper skin and the lower skin after the injection mold is closed;
s4, 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, forming a filling core after the foam plastic is molded, filling a notch in the filling core processing process, forming a strip-shaped bulge in the notch, realizing connection of a girder and the filling core through matching of the strip-shaped bulge and the notch, improving connection stability of the filling core and the girder, and installing a connecting structure at the end part of the girder as the girder passes through the end, which is not connected, of the upper skin and the lower skin after the filling core is molded, and installing the whole rotor blade on a hub;
s5, performing skin treatment on the end parts of the upper skin and the lower skin, wherein the materials used for the skins are the same as the materials used for manufacturing the upper skin and the lower skin;
s6, carrying out integral coating on the upper skin and the lower skin through the Kjeldahl, and finally coating a layer of skin on the surface of the Kjeldahl.
Preferably, the girder is arranged at the thicker end of the water drop-shaped cavity, the outer surface of the girder is attached to the inner surface of the upper skin and the inner surface of the lower skin, the girder is divided into two mirror symmetry side surfaces, in the mold closing process, the two side surfaces of the girder are attached to the inner bottom surfaces of the upper skin and the lower skin respectively, so that the girder is effectively fixed, and a filling core is distributed at one side of the girder and is positioned at the thinner end of the cavity, so that the design of the rotation center of gravity of the rotary wing piece is facilitated.
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, the end part of the first cavity, which is far away from the second cavity, is arranged into an arc shape, and the first cavity and the second cavity are arranged for controlling the rotation direction gravity center of the rotor wing to be on the width quarter point of the rotor wing, which is close to the thicker end.
Preferably, the upper skin and the lower skin are both made of glass fibers, and the surface-coated skin of the kevlar is made of carbon fibers.
Compared with the prior art, the invention has the following beneficial effects:
according to the processing technology of the rotorcraft rotor blade, the upper skin and the lower skin are processed through the die, so that other edges of the upper skin and the lower skin except one end for injection molding can be completely jointed, the manufactured upper skin and lower skin are respectively arranged in an upper die plate and a lower die plate of an injection die, a girder is used as an embedded part to be placed in a cavity between the upper skin and the lower skin, the edges of the upper skin and the lower skin are glued before die assembly, die assembly injection molding is performed, and finally one ends of the upper skin and the lower skin for injection molding are covered; the whole processing process omits the process of independently manufacturing and gluing the filler, reduces the production procedures and improves the production efficiency.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions of the prior art, the drawings that are needed in the embodiments will be briefly described below, it being obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic structural view of a rotorcraft rotor blade processed by the processing technique of the rotorcraft rotor blade of the present invention;
fig. 2 is a schematic cross-sectional view of a rotorcraft rotor blade processed by the rotorcraft rotor blade processing process of the present invention.
Reference numerals illustrate: 10. a girder; 11. a first cavity; 12. a second cavity; 13. a notch; 20. filling the core; 21. a bar-shaped protrusion; 30. an upper skin; 40. and a lower skin.
Detailed Description
Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative only and are not to be construed as limiting the invention.
In the description of the present invention, it should be understood that the terms "length," "width," "inner," "outer," and the like indicate an orientation or a positional relationship based on that shown in the drawings, and are merely for convenience of description and simplification of the description, and do not indicate or imply that the apparatus or element in question must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present invention, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.
As shown in fig. 1-2, in order to improve the production efficiency of the rotor wing, an embodiment of the present invention provides a processing technology of a rotor wing of a gyroplane, which includes the following steps:
s1, manufacturing a girder 10 through an aluminum alloy extrusion molding process, and cutting a section according to design requirements;
s2, respectively manufacturing an upper skin 30 and a lower skin 40 through a die, 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 die;
s3, inserting the girder 10 as an embedded part between the upper skin 30 and the lower skin 40, performing gluing treatment on 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 plastic into the cavity between the upper skin 30 and the lower skin 40 from the end surfaces of the upper skin 30 and the lower skin 40 through an injection mold, and forming the filling core 20 after the foam plastic is molded;
s5, performing skin treatment on the end parts of the upper skin 30 and the lower skin 40, wherein the materials used for the skins are the same as the materials used for manufacturing the upper skin 30 and the lower skin 40;
s6, the upper skin 30 and the lower skin 40 are integrally coated through the Kjeldahl, and finally a layer of epidermis is coated on the surface of the Kjeldahl.
In this embodiment, the upper skin 30 and the lower skin 40 are shaped by 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 into an upper mold set and a lower mold set of the injection mold; the mold closing process of the upper mold set and the lower mold set is that one mold set horizontally moves relative to the other mold set, the girder 10 is pre-buried in one skin before mold closing, and the girder 10 is subjected to surface gluing, so that 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 is carried out on the edge of the upper skin 30 or the lower skin 40, a slot for the girder 10 to pass through is reserved in the injection mold, meanwhile, the girder 10 is limited by the slot, one end of the girder 10 passes out from the unconnected end of the upper skin 30 and the lower skin 40, and after die assembly, foam plastic is injected into the cavity through a runner of the injection mold while the gluing between the upper skin 30 and the lower skin 40 is realized.
After the core 20 is formed, since the girder 10 passes through the end of the upper skin 30 and the lower skin 40, which is not connected, a connection structure can be installed at the end of the girder 10, and the entire rotor blade can be installed on the hub.
And finally, carrying out Kjeldahl coating on the upper skin 30 and the lower skin 40, carrying out skin coating on the end parts of the filling core 20, connecting the unconnected ends of the upper skin 30 and the lower skin 40, completing the processing of the whole rotor blade, omitting the process of independently manufacturing and cementing the filling core 20 in the whole processing process, and improving the processing efficiency of the rotor blade.
As shown in fig. 2, to facilitate stable installation of the girder 10, the girder 10 is disposed at a thicker end of the cavity in a drop shape, and an outer surface of the girder 10 is attached to inner surfaces of the upper skin 30 and the lower skin 40.
In this embodiment, on the surface design of the girder 10, the girder 10 is divided into two mirror symmetry sides, the two sides are respectively attached to the inner bottom surfaces of the upper skin 30 and the lower skin 40, during the processing of the core filling 20, the surface of the girder 10 is glued, during the mold closing of the core filling 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 core filling 20 is distributed on one side of the girder 10 (i.e. the thinner end of the cavity), so as to facilitate the design of the rotation center of gravity of the vane.
As shown in fig. 2, to provide stability of the vane, 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 thicker end of the cavity, and the end of the first cavity 11 far from the second cavity 12 is arranged in an arc shape.
In this embodiment, by arranging the first cavity 11 and the second cavity 12, the center of gravity of the turning direction of the turning vane is controlled to be on the quarter point of the width 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 arc-shaped, so that the stress stability of the first cavity 11 is enhanced.
As shown in fig. 1-2, to provide stability in the connection of the filling core 20 to the girder 10, a notch 13 is formed in the end of the girder 10 remote from the thicker end of the cavity, and the bottom surface of the notch 13 is wider than the top opening of the notch 13.
In this embodiment, the notch 13 with a narrow opening and a wide bottom is connected with the filling core 20, and during the processing of the filling core 20, the filling core 20 fills the notch 13, and a strip-shaped protrusion 21 is formed in the notch 13, so that the strip-shaped protrusion 21 is matched with the notch 13 to connect the girder 10 with the filling core 20, and the connection stability of the filling core 20 with the girder 10 is improved.
As a preferred embodiment of the present invention, in order to increase 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 carbon fiber. The glass fiber is used as a base material of the skin, and the kevlar is paved on the surface of the glass fiber, so that the strength of the rotary wing panel is improved, and the deformation of the rotary wing panel is avoided.
Finally, it is noted that the above embodiments are only for illustrating the technical solution of the present invention and not for limiting the same, and 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 and equivalents may be made thereto without departing from the spirit and scope of the technical solution of the present invention, which is intended to be covered by the scope of the claims of the present invention.
Claims (4)
1. A processing technology of a gyroplane rotor blade is characterized in that: the method comprises the following steps:
s1, manufacturing a girder (10) through an aluminum alloy extrusion molding process, and cutting a section according to design requirements;
s2, respectively manufacturing an upper skin (30) and a lower skin (40) through a die, and respectively placing the upper skin (30) and the lower skin (40) in an upper die set and a lower die set of an injection die after the upper skin (30) and the lower skin (40) are stable, wherein the die assembly process of the upper die set and the lower die set is that one die set horizontally moves relative to the other die set;
s3, inserting the girder (10) between the upper skin (30) and the lower skin (40) as an embedded part, and performing gluing treatment on the surface of the girder (10) so that the outer surface of the girder (10) is glued with the inner bottom surfaces of the upper skin (30) and the lower skin (40), the upper skin (30) and the lower skin (40) enclose a cavity with a water drop-shaped cross section, gluing the edge of the upper skin (30) or the lower skin (40), reserving a slot for the girder (10) to pass through in an injection mold, limiting the girder (10) by the slot, enabling one end of the girder (10) to pass out from the unconnected end of the upper skin (30) and the lower skin (40), enabling the end of the girder (10) far away from the thicker end of the cavity to be provided with a notch (13), enabling the bottom surface of the notch (13) to be wider than the top opening of the notch (13), and gluing the joint of the upper skin (30) and the lower skin (40) after the injection mold is closed;
s4, injecting foam plastic into a cavity between the upper skin (30) and the lower skin (40) from the end surfaces of the upper skin (30) and the lower skin (40) through an injection mold, forming a filling core (20) after the foam plastic is molded, filling the notch (13) with the filling core (20) in the processing process of the filling core (20), forming a strip-shaped bulge (21) in the notch (13), realizing the connection of the girder (10) and the filling core (20) through the matching of the strip-shaped bulge (21) and the notch (13), improving the connection stability of the filling core (20) and the girder (10), and after the filling core (20) is molded, installing a connecting structure at the end part of the girder (10) as the girder (10) passes through the end part of the upper skin (30) and the end surface of the lower skin (40), and installing the whole rotor wing on a slurry hub;
s5, performing skin treatment on the end parts of the upper skin (30) and the lower skin (40), wherein the materials used for the skins are the same as the materials 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 Kjeldahl, and finally coating a layer of epidermis on the surface of the Kjeldahl.
2. A process for manufacturing rotorcraft rotor blades, according to claim 1, characterized in that: the girder (10) is arranged at the thicker end of the water drop-shaped cavity, the outer surface of the girder (10) is attached to the inner surfaces of the upper skin (30) and the lower skin (40), the girder (10) is divided into two mirror symmetry side surfaces, in the mold closing process, the two side surfaces of the girder (10) are attached to the inner bottom surfaces of the upper skin (30) and the lower skin (40) respectively, so that the girder (10) is effectively fixed, and a filling core (20) is distributed on one side of the girder (10) and positioned at the thinner end of the cavity, so that the design of the rotation center of gravity of the rotary wing piece is facilitated.
3. A process for manufacturing rotorcraft rotor blades, according to claim 2, characterized in that: first cavity (11) and second cavity (12) have been seted up along the axial of girder (10) in girder (10), first cavity (11) are close to the thick end of cavity, just first cavity (11) are kept away from the tip of second cavity (12) sets up into the arc, first cavity (11) with the setting of second cavity (12) for control the rotation of wing piece is close to on the width quartering point of thick end in the wing piece.
4. A process for the manufacture of a rotorcraft rotor blade according to any one of claims 1 to 3, characterized in that: the upper skin (30) and the lower skin (40) are made of glass fibers, and the surface-coated surface of the kevlar is made of carbon fibers.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311797231.5A CN117799110A (en) | 2022-02-21 | 2022-02-21 | Processing technology of gyroplane rotor blade |
Applications Claiming Priority (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 |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210157196.XA Division CN114571663A (en) | 2022-02-21 | 2022-02-21 | Processing technology of rotary wing panel of gyroplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117799110A true CN117799110A (en) | 2024-04-02 |
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Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210157196.XA Pending CN114571663A (en) | 2022-02-21 | 2022-02-21 | Processing technology of rotary wing panel of gyroplane |
| CN202311797231.5A Pending CN117799110A (en) | 2022-02-21 | 2022-02-21 | Processing technology of gyroplane rotor blade |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210157196.XA Pending CN114571663A (en) | 2022-02-21 | 2022-02-21 | Processing technology of rotary wing panel of gyroplane |
Country Status (1)
| Country | Link |
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| CN (2) | CN114571663A (en) |
Family Cites Families (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 |
| DE2304213C2 (en) * | 1972-02-14 | 1983-01-13 | United Technologies Corp., 06101 Hartford, Conn. | Rotor blade and method of making the same |
| JP5503481B2 (en) * | 2010-09-30 | 2014-05-28 | 一般社団法人日本航空宇宙工業会 | Wing-like structure using fiber-reinforced composite material and manufacturing method thereof |
| 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 |
| CN109228375B (en) * | 2018-11-01 | 2023-08-18 | 成都纵横大鹏无人机科技有限公司 | Skin forming method |
| CN112238551B (en) * | 2020-09-27 | 2022-04-12 | 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 CN202210157196.XA patent/CN114571663A/en active Pending
- 2022-02-21 CN CN202311797231.5A patent/CN117799110A/en active Pending
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| Publication number | Publication date |
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| CN114571663A (en) | 2022-06-03 |
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