CN214927268U - A Helicopter Tail Boom Mould - Google Patents
A Helicopter Tail Boom Mould Download PDFInfo
- Publication number
- CN214927268U CN214927268U CN202121166966.4U CN202121166966U CN214927268U CN 214927268 U CN214927268 U CN 214927268U CN 202121166966 U CN202121166966 U CN 202121166966U CN 214927268 U CN214927268 U CN 214927268U
- Authority
- CN
- China
- Prior art keywords
- core
- tail beam
- mold
- mould
- composite material
- 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.)
- Active
Links
Images
Landscapes
- Moulds For Moulding Plastics Or The Like (AREA)
Abstract
本实用新型涉及一种直升机尾梁模具，包括芯模和外模，芯模包括底座以及可拆卸的固定于底座之上的主体分芯模，主体分芯模的上端部可拆卸的固定有连接体，连接体的四周可拆卸的固定分布有两对端部分芯模，以及盖于连接体上部的上端板；组装芯模后的外表面结构与复合材料尾梁制件的内型面结构相匹配，芯模的外表面用于铺贴形成复合材料尾梁预制体；外模由两个对称的分外模构成，组装外模后的内表面结构与复合材料尾梁制件的外型面结构相匹配，外模用于将所述复合材料尾梁预制体进行固化制成复合材料尾梁制件。本实用新型的尾梁模具能够实现复合材料尾梁的一体成型，并保证复合材料尾梁的气动外表面具有较好的质量。
The utility model relates to a helicopter tail beam mould, which comprises a core mould and an outer mould. The core mould comprises a base and a main part core mould detachably fixed on the base; the upper end of the main part core mould is detachably fixed with a connection There are two pairs of end part core molds detachably and fixedly distributed around the connecting body, and an upper end plate covering the upper part of the connecting body; the outer surface structure after assembling the core mold is consistent with the inner surface structure of the composite material tail beam part. Matching, the outer surface of the core mold is used for paving to form a composite tail beam prefab; the outer mold is composed of two symmetrical separate outer molds, and the inner surface structure after assembling the outer mold and the outer surface of the composite tail beam part The structure is matched, and the outer mold is used to solidify the composite tail beam prefab to form a composite tail beam product. The tail beam mold of the utility model can realize the integral molding of the composite material tail beam, and ensure that the aerodynamic outer surface of the composite material tail beam has good quality.
Description
Technical Field
The utility model relates to a mould field of making, concretely relates to helicopter tail boom mould.
Background
The helicopter body structure mainly comprises a helicopter body and a tail beam, wherein the tail beam is used for supporting a speed reducer and fixing a horizontal stabilizing surface. The composite material tail beam has the characteristics of light weight, high rigidity and low cost, and becomes a popular novel helicopter tail beam structure.
The existing composite material tail beam is formed by connecting a left half tail beam and a right half tail beam through glue rivets by an assembling tool, and the assembling tool and the assembling process are increased. To ensure overall strength and rigidity, a large number of structural glues need to be applied and a large number of fasteners installed, resulting in an increase in the weight of the tail boom. The integrally formed composite material has less parts, no need of assembly and light weight, but requires smooth pneumatic outer surface, so that the composite material cannot be directly formed by a male die. Because the section size of the tail beam is small, the tail beam can not be directly molded by a female die. There is a need for a simple, easy to operate mold that ensures aerodynamic outer surface of the tail boom and a method for manufacturing the tail boom at low cost.
SUMMERY OF THE UTILITY MODEL
In order to solve the technical problem that the assembly process of the existing tail beam is complex, a helicopter tail beam mold is provided. The utility model discloses the integrated into one piece of combined material tail-boom finished piece can be realized to the tail-boom mould to reduce the input of assembly fixture, reduce the assembly link, reduce the quantity that fastener and structure were glued, further lighten the weight of combined material tail-boom finished piece. Through the utility model discloses can realize the low-cost manufacturing of combined material tail boom finished piece and guarantee the pneumatic surface of combined material tail boom finished piece.
In order to achieve the above purpose, the utility model discloses a following technical scheme realizes:
a helicopter tail beam mold comprises a core mold and an outer mold, wherein the core mold comprises a base and a main body core dividing mold detachably fixed on the base, a connecting body is detachably fixed at the upper end of the main body core dividing mold, two pairs of end part core molds and an upper end plate covering the upper part of the connecting body are detachably and fixedly distributed on the periphery of the connecting body; the outer surface structure of the assembled core die is matched with the inner profile structure of the composite material tail beam part, and the outer surface of the core die is used for paving and pasting to form a composite material tail beam prefabricated body;
the outer die is composed of two symmetrical outer dies, the inner surface structure of the outer die is matched with the outer surface structure of the composite material tail beam part after the outer die is assembled, and the outer die is used for curing the composite material tail beam prefabricated part to manufacture the composite material tail beam part.
Further, the main body core dividing mold is of a circular truncated cone-shaped structure, a concave surface is arranged on the main body core dividing mold, and the structure of the concave surface corresponds to the inner profile surface of the composite material tail beam workpiece with the shaped honeycomb; the connector is of a cuboid structure; one of the end section core molds has a pair of tabs with an end structure of a composite tail boom piece; the upper end plate has an outwardly extending portion which is aligned with the projections when the core is assembled for closing the opening formed by the two pairs of end section cores.
Still further, the main part divides the core mould to be fixed in on the bottom plate, the bottom plate detachable is fixed in on the base.
Furthermore, the parts on the core mold and the parts on the outer mold are fixed in a detachable fixing mode through bolts.
Further, the core mold is made of one of aluminum alloy, wood substitute, glass fiber composite material and carbon fiber composite material. Other materials which are light, pressure-resistant and uneasy to deform can be used.
Furthermore, the outer die is made of one of a steel material, a glass fiber composite material and a carbon fiber composite material.
Furthermore, the shell frame of the external mold with the cavity is a hollow support structure after assembly.
The method for preparing the integrally-formed composite material tail beam by using the helicopter tail beam mold comprises the following steps:
(1) assembling and fixing the core mould according to a matching relation, and coating a release agent on the outer surface of the core mould and the inner surface of the outer mould;
(2) firstly paving an adhesive film on the outer surface of the core mold, splicing a honeycomb structure material on the concave surface of a main body core parting mold of the core mold, reserving a butt seam along the axial direction, filling foaming adhesive at the seam generated by splicing, then making a bag, carrying out curing treatment to obtain a shaped honeycomb, and taking down the shaped honeycomb;
(3) cleaning the core mold, coating a release agent, paving and pasting cut inner skin prepreg on the outer surface of the core mold according to the appearance structure of the composite material tail beam workpiece, paving and pasting an adhesive film, making a bag and performing pre-compaction; placing the shaped honeycomb on the concave surface of the main body core splitting mold of the core mold, paving a glue film, making a bag and performing pre-compaction; then, paving and pasting the cut outer skin prepreg on the outer surface of the core mold, and performing bag making and pre-compaction; obtaining a composite material tail beam prefabricated body, and then demoulding;
(4) and (3) attaching the outer profile of the composite material tail beam prefabricated part to the inner surface of one of the split outer molds, assembling and fixing the outer molds, curing after bag making, cooling after curing, disassembling the outer molds, and demolding to obtain the composite material tail beam workpiece.
Further, the demolding process in the step (3) is to freeze the core mold with the composite material tail beam prefabricated body at-18 ℃, and to disassemble the core mold after the composite material tail beam prefabricated body is hardened.
The beneficial technical effects are as follows:
the utility model discloses a mandrel equipment is convenient, and the shop of the preform of being convenient for pastes, and the preform is spread and is pasted the completion back, can follow the mandrel fast and take off, the site operation of being convenient for. The outer die can effectively ensure the quality of the outer surface of the composite material tail beam workpiece. Utilize the utility model discloses a mould and method can realize the integrated into one piece of combined material tail-beam finished piece, reduce assembly link and fastener quantity, further alleviate the weight of combined material tail-beam finished piece.
Drawings
Fig. 1 is an exploded view of a core mold.
Fig. 2 is a schematic assembled core mold.
Fig. 3 is a schematic diagram of the outer mold after assembly.
Fig. 4 is a cross-sectional view of the outer mold.
FIG. 5 is a diagram of the profile of a composite tail boom article.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely below with reference to the embodiments of the present invention and the accompanying drawings, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
Unless specifically stated otherwise, the numerical values set forth in these examples do not limit the scope of the present invention. Techniques, methods known to those of ordinary skill in the relevant art may not be discussed in detail, but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values.
Example 1
A helicopter tail beam mould comprises a core mould and an outer mould, wherein the explosion structure of the core mould is shown in figure 1, and the assembled schematic view of the core mould is shown in figure 2; the schematic diagram of the assembled external mold is shown in FIG. 3, and the sectional view of the external mold is shown in FIG. 4;
the core mould comprises a base 1 and a main body core dividing mould 2 which is detachably fixed on the base 1, a connector 5 is detachably fixed at the upper end of the main body core dividing mould 2, two pairs of end part core moulds 3 and 4 and an upper end plate 6 covering the upper part of the connector 5 are detachably and fixedly distributed on the periphery of the connector 5; the outer surface structure of the assembled core die is matched with the inner profile structure of the composite material tail beam part, and the outer surface of the core die is used for paving and pasting to form a composite material tail beam prefabricated body; the composite material tail beam prefabricated body is formed by sequentially stacking and pressing an inner skin prepreg, a shaped honeycomb and an outer skin prepreg, and the structure of the composite material tail beam prefabricated body is a honeycomb sandwich structure;
the outer die is composed of two symmetrical outer dies 7, the outer die is provided with a cavity after being assembled, a shell frame of the outer die is a hollow supporting structure, the inner surface structure of the outer die after being assembled is matched with the outer surface structure of the composite material tail beam part, and the outer die is used for curing the composite material tail beam prefabricated part to manufacture the composite material tail beam part;
the main body core splitting mold 2 is of a circular truncated cone-shaped structure, a concave surface is arranged on the main body core splitting mold 2, the structure of the concave surface corresponds to the structure of a sandwich area with a shaped honeycomb on the inner molded surface of a tail beam workpiece made of a composite material, the main body core splitting mold 2 is fixed on a bottom plate 21, and the bottom plate 21 is detachably fixed on a base 1; the connector 5 is of a cuboid structure; one pair 3 of the end section core molds has a lug 31 of the end structure of the composite tail boom piece; the upper end plate 6 has an outwardly extending portion 61, and the extension portion 61 is aligned with the protrusion 31 when the core mold is assembled, so as to close the opening formed by enclosing the two pairs of end portion core molds 3, 4;
the parts on the core mold are connected in a bolt fixing mode, and the two sub-outer molds 7 are fixedly connected by bolts;
the core mold is made of one of aluminum alloy, wood substitute, glass fiber composite material and carbon fiber composite material, and other materials which are light, pressure-resistant and difficult to deform can be adopted; the outer mold is made of one of a steel material, a glass fiber composite material and a carbon fiber composite material.
Divide into two pairs in this embodiment, four fritters of tip mandrel 3, 4 and distribute around connector 5, mainly according to the structure of combined material tail boom finished piece and decide to and relate to the problem of how to be convenient for the drawing of patterns, the utility model provides a combined material tail boom finished piece is special-shaped structure, has binding off, if the piece number of tip mandrel split is less than four, then is unfavorable for the dismantlement after the equipment and the drawing of patterns of material on the mandrel.
Example 2
A method of making an integrally formed composite tail boom article using the helicopter tail boom mold of embodiment 1 comprising the steps of:
(1) fixing the main body core splitting mold 2 on the base 1 through four bolts on the bottom plate 21 according to a matching relationship; then fixing the connecting body 5 at the center of the main body core parting mold 2 through two positioning pins and four bolts; fixing two pairs of end part core moulds 3 and 4 around a connecting body 5 above the main body part core mould 2, wherein one pair of end part core moulds 3 is provided with a projection 31 with a tail beam end structure, the two pairs of end part core moulds 3 and 4 are respectively connected with a connecting box through two pins and three bolts, and the connecting body 5 and the two pairs of end part core moulds 3 and 4 are assembled above the main body part core mould 2; then, installing an upper end plate 6 having an extension 61, aligning the extension 61 with the protrusion 31 during assembly, and closing the opening formed by enclosing the two pairs of end section core molds 3 and 4 by the upper end plate 6, thereby completing the assembly and fixation of the core molds;
then coating a release agent on the outer surface of the core mold and the inner surface of the outer mold;
(2) firstly paving an adhesive film on the outer surface of the core mold, splicing a honeycomb structure material on the concave surface of the main body core parting mold 2 of the core mold, reserving a butt joint along the axial direction, filling foaming adhesive at the joint generated by splicing, then making a bag, carrying out curing treatment to obtain a shaped honeycomb, and taking down the shaped honeycomb;
(3) cleaning the core mould, coating a release agent, paving and pasting the cut inner skin prepreg on the outer surface of the core mould according to the appearance structure of the composite material tail beam workpiece, paving a layer of adhesive film, and pre-compacting for 10min after bag making; placing the shaped honeycomb on the concave surface of the main body core-dividing mold 2 of the core mold, paving an adhesive film, making a bag, and performing pre-compaction for 15 min; then, paving and pasting the cut outer skin prepreg on the outer surface of the core mold, and performing bag making and pre-compaction for 15 min; obtaining a composite material tail beam prefabricated body, and then demoulding, wherein the demoulding process is to freeze a core mould with the composite material tail beam prefabricated body at the temperature of-18 ℃, after the composite material tail beam prefabricated body is hardened, sequentially disassembling an upper end plate 6, a connecting body 5 and end part core moulds 3 and 4 of the core mould, and taking down the hardened composite material tail beam prefabricated body;
in the step, the inner skin prepreg is paved according to a paving sequence [45/0/45 ]; paving and pasting the outer skin prepreg according to a paving sequence [45/0/45/0/45/0/45 ];
(4) according to the shape of the tail beam, the outer shape surface of the composite tail beam prefabricated body is attached to the inner surface of one of the split outer molds 7, then the other split outer mold 7 is attached, the composite tail beam prefabricated body is attached to a cavity formed by assembling the outer molds, and the two split outer molds 7 are fixed through locking of bolts;
and then placing the tubular vacuum bag into an outer model cavity (namely the vacuum bag is in the cavity of the prefabricated body) which is attached with the composite material tail beam prefabricated body, attaching sealing rubber strips at two ends of the outer mold and a mold closing gap to seal the vacuum bag, installing a vacuumizing and vacuum measuring pipeline, placing the vacuum bag in a curing furnace to perform vacuumizing curing, cooling the vacuum bag to room temperature after curing is completed, disassembling the outer mold, taking down the outer mold, and demolding to obtain the composite material tail beam part.
The structure of the tail beam part made of the composite material is shown in fig. 5, wherein a tail beam body 8 is a truncated cone-shaped hollow structure, the structure of the tail beam body 8 is a honeycomb sandwich structure (which is composed of an inner skin, a shaped honeycomb and an outer skin from inside to outside and is provided with a sandwich region structure of the shaped honeycomb), and a sandwich region on the inner surface of the tail beam body 8 corresponds to the concave surface of the shape of the main body core splitting mold 2; the end structure 9 corresponds to the projection 31 of the end plug 3.
Comparative example 1
The method for manufacturing the integrally formed composite tail beam of the present comparative example is the same as that of example 2, except that the composite tail beam preform is not taken off from the core mold in the step (3), and the outer mold is directly attached and assembled outside the core mold with the composite tail beam preform.
The composite material tail beam part obtained in the comparative example and the composite material tail beam part obtained in the example 2 are subjected to quality detection, and comparative items are shown in table 1.
Table 1 results of quality inspection of composite tail boom parts manufactured in comparative example 1 and example 2
As can be seen from Table 1, the composite material tail beam part prepared by the method of the invention has better internal quality and external surface quality. The preparation method of example 2 is that the composite tail beam prefabricated body is taken off from the core mould, then is frozen and hardened and transferred to the external mould to be solidified and formed, and the external mould is not directly sleeved on the core mould with the prefabricated body to be solidified, because: theoretically, the thickness of the gap between the outer die and the core die is the thickness of the composite material tail beam part, but in practice, the thickness of the laid prefabricated part is difficult to control to reach the thickness of the gap, so that the internal quality and the external surface of the composite material tail beam part have the defects of comparative example 1 in the table 1 after the outer die is directly sleeved on the core die with the prefabricated part for curing; in the invention, the composite material tail beam prefabricated body is taken down from the core mould, then is subjected to freezing hardening and is transferred to the outer mould for curing and forming, so that the defect of poor internal quality and external surface quality can be avoided, the low-cost manufacturing is realized, and meanwhile, the pneumatic external surface of the composite material tail beam part is ensured.
The utility model discloses the integrated into one piece of combined material tail-boom finished piece can be realized to the tail-boom mould to reduce the input of assembly fixture, reduce the assembly link, reduce the quantity that fastener and structure were glued, further lighten the weight of combined material tail-boom finished piece.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can substitute or change the technical solution and the inventive concept of the present invention within the technical scope of the present invention.
Claims (7)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121166966.4U CN214927268U (en) | 2021-05-28 | 2021-05-28 | A Helicopter Tail Boom Mould |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121166966.4U CN214927268U (en) | 2021-05-28 | 2021-05-28 | A Helicopter Tail Boom Mould |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214927268U true CN214927268U (en) | 2021-11-30 |
Family
ID=79060185
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121166966.4U Active CN214927268U (en) | 2021-05-28 | 2021-05-28 | A Helicopter Tail Boom Mould |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214927268U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113183487A (en) * | 2021-05-28 | 2021-07-30 | 常州启赋安泰复合材料科技有限公司 | Helicopter tail beam mold and method for preparing integrally-molded composite tail beam workpiece |
| CN116061462A (en) * | 2022-11-28 | 2023-05-05 | 西安电子工程研究所 | A hat-shaped reinforced structure full-carbon fiber radar servo base forming mold and method |
| CN116118056A (en) * | 2022-12-14 | 2023-05-16 | 航天神舟飞行器有限公司 | Composite material air inlet channel product forming tool based on memory core die |
-
2021
- 2021-05-28 CN CN202121166966.4U patent/CN214927268U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113183487A (en) * | 2021-05-28 | 2021-07-30 | 常州启赋安泰复合材料科技有限公司 | Helicopter tail beam mold and method for preparing integrally-molded composite tail beam workpiece |
| CN113183487B (en) * | 2021-05-28 | 2024-10-11 | 常州启赋安泰复合材料科技有限公司 | A helicopter tail beam mold and a method for preparing an integrally formed composite tail beam component |
| CN116061462A (en) * | 2022-11-28 | 2023-05-05 | 西安电子工程研究所 | A hat-shaped reinforced structure full-carbon fiber radar servo base forming mold and method |
| CN116118056A (en) * | 2022-12-14 | 2023-05-16 | 航天神舟飞行器有限公司 | Composite material air inlet channel product forming tool based on memory core die |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN214927268U (en) | A Helicopter Tail Boom Mould | |
| CN109895418B (en) | Processing method of special-shaped hollow structure composite material part forming core mold | |
| CN113829638B (en) | Integrated molding method for composite material cabin section | |
| CN108891040B (en) | A kind of manufacturing method of composite material horizontal tail for small and medium-sized unmanned aerial vehicle | |
| CN108407332B (en) | Compression molding method for composite material grid skin structural part | |
| JPH03104799A (en) | Manufacture of composite material blade | |
| CN111391362A (en) | Thermal expansion and compression molding method of UAV composite material flat tail silicone rubber | |
| CN110510145A (en) | A three-beam composite wing integral structure and its forming process method | |
| CN115464899B (en) | A composite material forming method for a hollow rotating body structure with front and rear ends | |
| CN110193957A (en) | A kind of small drone composite aileron moulding technique | |
| CN113997598A (en) | Composite material thin-wall reinforcing rib forming die and reinforcing rib integrated forming method | |
| CN113183487A (en) | Helicopter tail beam mold and method for preparing integrally-molded composite tail beam workpiece | |
| CN105690821A (en) | Wet winding forming method for fiber-reinforced resin matrix composite sandwich pipe | |
| CN110303693A (en) | A kind of compression-moulding methods of small-sized aerofoil Composite Sandwich part | |
| CN113977984B (en) | Preparation method of tubular hyperboloid composite structural member | |
| CN115742367A (en) | High-modulus carbon fiber composite main frame, preparation method and preparation mold | |
| CN118544611B (en) | Preparation method and product of light auxiliary frame of automobile composite material | |
| CN117207552B (en) | Layering method and forming die for compression molding sandwich composite material piece | |
| CN113858655B (en) | Unmanned aerial vehicle lightweight engine body tool and engine body development method | |
| CN115674728B (en) | Die for forming inner and outer skins and sandwich integrated tube and use method thereof | |
| CN119174312B (en) | Thermal expansion die auxiliary forming process of composite flange | |
| TWI530419B (en) | Method for forming core shell layer of carbon fiber bicycle and the forming structure thereof | |
| CN118664931A (en) | A method and device for forming a composite material structure of a thick tube beam with a male and female mold combination | |
| CN115107296A (en) | Die and method for integrally forming head conical part with smooth inner and outer surfaces | |
| CN114083812A (en) | A composite multi-rotor unmanned aerial vehicle integral molding mold and method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 213032 No.202 Donghai Road, Xinbei District, Changzhou City, Jiangsu Province Patentee after: Kotai Si Innovation Technology (Jiangsu) Co., Ltd. Country or region after: China Address before: 213032 No.202 Donghai Road, Xinbei District, Changzhou City, Jiangsu Province Patentee before: Changzhou Qifu Antai Composite Technology Co.,Ltd. Country or region before: China |