CN223701782U - A tooling for co-curing and co-bonding aircraft composite control surfaces - Google Patents

A tooling for co-curing and co-bonding aircraft composite control surfaces

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Publication number
CN223701782U
CN223701782U CN202423239111.6U CN202423239111U CN223701782U CN 223701782 U CN223701782 U CN 223701782U CN 202423239111 U CN202423239111 U CN 202423239111U CN 223701782 U CN223701782 U CN 223701782U
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China
Prior art keywords
mold
forming mold
rib
die
control surface
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CN202423239111.6U
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Chinese (zh)
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柳毅
岳云江
何平
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Jiangsu Meilong Aviation Components Co ltd
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Jiangsu Meilong Aviation Components Co ltd
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    • 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

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  • Moulds For Moulding Plastics Or The Like (AREA)

Abstract

本实用新型公开了一种飞机复材舵面的共固化再共胶接成型工装，上主体模上根据舵面上表面设置上蒙皮成型模，下主体模上根据舵面下表面设置下蒙皮成型模，下蒙皮成型模上方设置肋成型模，下蒙皮成型模侧方设置梁成型模，下蒙皮成型模左端根据舵面左表面设置左模，下蒙皮成型模右端根据舵面右表面设置右模，左模左侧设置脱模板安装，右模右侧设置加力板，上主体模与下主体模之间设置定位导柱合模。针对先共固化制造复材框架组件，再在复材框架组件上将蒙皮和蜂窝芯以共胶接结合成型的飞机复材舵面的成型工艺，该成型工装上可兼顾完成共固化再共胶接，可拆分的模具使得可对多个肋和梁定位准确，并且可拆卸脱模，有利于提高产品质量。

This utility model discloses a co-curing and co-bonding molding fixture for aircraft composite control surfaces. An upper skin forming mold is set on the upper main mold according to the upper surface of the control surface, and a lower skin forming mold is set on the lower main mold according to the lower surface of the control surface. A rib forming mold is set above the lower skin forming mold, and a beam forming mold is set to the side of the lower skin forming mold. A left mold is set at the left end of the lower skin forming mold according to the left surface of the control surface, and a right mold is set at the right end of the lower skin forming mold according to the right surface of the control surface. A demolding template is set on the left side of the left mold, and a force-adhesive plate is set on the right side of the right mold. A positioning guide post is set between the upper and lower main molds for mold closing. For the molding process of aircraft composite control surfaces where a composite frame assembly is first co-cured and then the skin and honeycomb core are co-bonded onto the composite frame assembly, this molding fixture can simultaneously complete co-curing and co-bonding. The detachable mold allows for accurate positioning of multiple ribs and beams, and the demolding is easy, which helps improve product quality.

Description

Co-curing and then co-cementing forming tool for aircraft composite control surface
Technical Field
The utility model relates to a forming tool for a composite control surface of an aircraft, in particular to a forming tool in a co-curing and then co-cementing forming mode.
Background
Some supersonic unmanned aerial vehicles adopt honeycomb sandwich composite material structures, and a plurality of ribs and main beams are arranged to improve structural strength in a co-curing connection mode.
In general, for the composite control surface of an aircraft, a structure is shown in figure 1, a composite frame assembly is formed by a beam, an upper rib, a middle rib, a lower rib and a twisted strip filling block, a composite control surface assembly is formed by a skin, a honeycomb core, a composite frame assembly and a structural adhesive film layer, and the composite control surface assembly is formed by adopting a co-bonding mode and a secondary bonding mode. However, the composite control surface for the supersonic unmanned aerial vehicle needs to meet the requirements that the plane bears larger bending, shearing and torsion on the rib and the beam when in supersonic flight during design, but the rigidity and strength of the beam-rib connection can not meet the bearing requirements in a common co-cementing or secondary cementing forming mode, and the temperature resistance requirement of the plane surface is quite high when in supersonic flight, and the following defects exist:
1. Because the aircraft composite control surface adopts a supercritical wing shape, the control surface is of a hyperboloid structure, the included angle between the upper rib edge, the lower rib edge and the middle web plate of the box-shaped rib is smaller than 90 degrees, and the molding difficulty of the mold is high;
2. The space distance between the ribs is small, and the rib is difficult to demold when the combined die is used;
3. Because the composite material control surface contains a plurality of ribs and beams, the mutual position positioning is difficult.
The co-cured composite frame component is designed for forming in the form of co-bonding the composite skin and the honeycomb core, and corresponding forming tools are designed for the co-cured composite frame component.
Disclosure of utility model
The utility model aims to provide a forming tool for an aircraft composite control surface, which is suitable for forming in a mode of co-bonding composite skins and honeycomb cores by adopting a co-cured composite frame component.
The technical scheme is that the co-curing and then co-bonding forming tool for the aircraft composite control surface comprises an upper main body die and a lower main body die which are oppositely arranged, wherein an upper skin forming die is arranged on the upper main body die according to the upper surface of the control surface, a lower skin forming die is arranged on the lower main body die according to the lower surface of the control surface, a rib forming die is arranged above the lower skin forming die, a beam forming die is arranged on the side of the lower skin forming die, a left die is arranged at the left end of the lower skin forming die according to the left surface of the control surface, a right die is arranged at the right end of the lower skin forming die according to the right surface of the control surface, a stripper plate is arranged at the left side of the left die and is installed on the lower main body die, a gusset plate is arranged at the right side of the right die and a positioning guide pillar is arranged between the upper main body die and the lower main body die for die closing;
When the composite control surface component is manufactured by co-bonding, the upper main body mould, the lower main body mould, the upper skin forming mould, the lower skin forming mould, the rib forming mould, the beam forming mould, the left mould, the right mould, the stripper plate and the gusset plate are used.
Further, the upper skin forming die and the lower skin forming die are respectively arranged into an upper block, a middle block and a lower block, the upper surface of the control surface and the lower surface of the control surface are respectively arranged into a middle block, the die assembly gaps between the upper block, the middle block and the lower block are respectively not more than 0.1mm, and the die assembly joints are respectively not more than 0.1mm.
Further, a die clamping gap between the upper main body die and the lower main body die is not more than 0.2mm.
Further, the rib forming die is arranged in a block mode according to the length direction of the control surface, the die closing gaps among the blocks are respectively not more than 0.1mm, and the positioning tolerance between the rib forming die and the lower main body die is +/-0.1 mm.
Furthermore, when the composite control surface component is manufactured by co-cementing, drill templates are arranged on the lower skin forming die, the rib forming die and the beam forming die and used for positioning the composite frame component when the composite frame component is co-cemented with the skin.
Further, according to the big end of the control surface, a die opening plate and a drawing screw rod which are connected with the end part of the beam forming die are arranged on the lower main body die so as to take out the beam forming die during demoulding.
The composite frame assembly has the advantages that aiming at the forming process of the aircraft composite control surface formed by co-bonding the skin and the honeycomb core on the composite frame assembly by co-curing, the designed forming tool can finish co-curing and then co-bonding, and the detachable die can accurately position a plurality of ribs and beams, can be detached for demolding, and is beneficial to improving the product quality.
Drawings
FIG. 1 is a schematic diagram of a composite control surface assembly;
FIG. 2 is an exploded view of the main structure of the forming tool of the present utility model;
FIG. 3 is a schematic view of a lower skin molding die structure;
FIG. 4 is a schematic diagram of the closing of the upper and lower body molds;
FIG. 5 is a schematic diagram showing a rib molding die layout.
Detailed Description
The utility model is further elucidated below in connection with the drawings and the specific embodiments.
The aircraft composite control surface has a structure shown in figure 1, and is composed of a beam 1-1, an upper rib 1-2, a middle rib 1-3 (two middle ribs are respectively marked as a middle rib 1-31 and a middle rib 1-32 in the figure), a lower rib 1-4 and a twisted strip filling block 1-5, wherein a composite frame assembly is formed by a skin 1-6, a honeycomb core 1-7 (three honeycomb cores are respectively marked as a honeycomb core 1-71, a honeycomb core 1-72 and a honeycomb core 1-73 in the figure), a composite frame assembly and a structural adhesive film layer, and the composite control surface is manufactured by a co-curing and co-bonding manufacturing method.
Step 100, co-curing to manufacture a composite frame assembly, specifically comprising the following steps 101-105.
And 101, cutting and blanking each layer of prepreg for manufacturing the beam, the upper rib, the middle rib, the lower rib, the twisted strip filling block and the skin according to the design size, and marking, wherein the prepreg is made of a T800 phthalonitrile carbon fiber unidirectional tape.
And 102, finishing the laying and compaction of each layer of prepreg on a beam forming die, wherein the laying information is (45/-45/0/90/45/-45/0/90) s, each 1-3 layers of prepreg are pre-compacted by a vacuum bag during laying, the laying angle is 0 DEG or 90 DEG or +/-45 DEG, the layers are laid in a staggered manner, and the splicing positions of the prepregs are staggered.
The production of the upper rib, the middle rib and the lower rib is completed on the respective forming dies with reference to the production of the beams.
Twisting the prepreg into twisted filaments to prepare twisted sub-strip filling blocks.
And 103, moving the well-paved beam, upper rib, middle rib, lower rib and twisted strip filling blocks into a closed combined die, artificially heightening the beam, the upper rib, the middle rib and the lower rib in the die by using a skin false piece, achieving that the appearance of the co-cured composite frame assembly is consistent with the design appearance, and pre-compacting after fixing the positions.
And 104, pre-compacting the combined and positioned composite frame assembly prefabricated body, trimming the surface of the prefabricated body, packaging and bagging, detecting the air tightness of the packaged bag after packaging and bagging, and then sending the packaged bag into an autoclave for curing and forming.
And 105, demolding, taking out the composite frame assembly, performing bolt drawing auxiliary demolding by using a demolding tool, trimming the appearance of the composite frame assembly after demolding, removing excessive burrs, wiping with acetone for decontamination, and sealing for later use after air drying.
Step 200, co-bonding to manufacture a composite control surface assembly, specifically comprising the following steps 201 to 205.
Step 201, manufacturing a honeycomb core according to the design size, wherein the honeycomb core is made of a phthalonitrile resin impregnated glass fiber honeycomb core.
And 202, finishing the laying and compaction of each layer of prepreg on a forming die of the skin, wherein the laying information is (45/-45/0/90/45/-45/0/0/-45/45/90/0/-45/45), each 1-3 layers of prepreg are pre-compacted by a vacuum bag during laying, the laying angle is 0 DEG or 90 DEG or +/-45 DEG, the layers are laid in a staggered manner, and the splicing positions of the prepregs are staggered.
And 203, moving the paved skin, the manufactured honeycomb core and the clean and modified composite frame assembly into a closed combined die, and performing gluing combination by using a high-temperature-resistant structural adhesive film layer.
And 204, packaging and bagging the combined and positioned composite material control surface assembly prefabricated body, detecting the air tightness of the packaged bag after packaging and bagging, and then sending the packaged bag into an autoclave for curing and forming.
And 205, demolding and taking out the composite control surface assembly.
The manufacturing method comprises the steps of manufacturing the composite frame assembly in a co-curing mode, and then bonding and forming the skin and the honeycomb core on the composite frame assembly in a co-bonding mode. The method for forming the co-cured and co-glued composite frame assembly is beneficial to the structural stability and strength improvement of the product, and the positioning of a plurality of ribs and beams is accurate when the composite frame assembly is co-cured, and the integral demolding is convenient after the co-curing is completed by means of the skin false piece.
The utility model relates to a forming tool capable of realizing the manufacturing method.
As shown in fig. 2, the upper main body die 1 and the lower main body die 2 are oppositely arranged, an upper skin forming die is arranged on the upper main body die 1 according to the upper surface of a control surface, a lower skin forming die is arranged on the lower main body die 2 according to the lower surface of the control surface, a rib forming die 3 is arranged above the lower skin forming die, a beam forming die 4 is arranged on the side of the lower skin forming die, a left die 5 is arranged at the left end of the lower skin forming die according to the left surface of the control surface, a right die 6 is arranged at the right end of the lower skin forming die according to the right surface of the control surface, a stripper 7 is arranged at the left side of the left die 5 and is mounted on the lower main body die 2, and a gusset 8 is arranged at the right side of the right die 6 and is mounted on the lower main body die 2.
When the composite material control surface component is manufactured by adopting a compression molding process, the upper main body die 1, the lower main body die 2, the rib forming die 3, the beam forming die 4, the left die 5, the right die 6, the stripper plate 7 and the gusset plate 8 are taken, the rib forming die 3 and the lower main body die 2 are connected by a rib positioning piece 31, the rib stripping die 32 is arranged between the rib forming die 3 and the lower main body die 2, and when the composite material control surface component is manufactured by adopting a compression molding process, the upper main body die 1, the lower main body die 2, the upper skin forming die, the lower skin forming die, the rib forming die 3, the beam forming die 4, the left die 5, the right die 6, the stripper plate 7 and the gusset plate 8 are taken.
As shown in fig. 3, the lower skin forming die 21 is provided with a combined die structure of an upper block 21-1, a middle block 21-2 and a lower block 21-3, wherein the middle block is used for forming the lower surface of the control surface, the upper block and the lower block can be freely split on two sides for disassembly and demolding, the die assembly gaps among the three blocks are respectively not more than 0.1mm, and the die assembly joints are respectively not more than 0.1mm. The upper skin forming die is similar to the lower skin forming die in arrangement.
As shown in fig. 4, a positioning guide post is arranged between the upper main body die 1 and the lower main body die 2 for positioning so as to assist in die assembly, a die assembly gap is not more than 0.2mm, and bolts are uniformly and tightly arranged around the upper main body die and the lower main body die so as to fasten by the bolts and be used for pressure curing.
The upper main body die, the lower main body die, the upper skin forming die and the lower skin forming die are made of Q345 steel, films are adhered to the outer surfaces of the dies, the thickness of the die walls is uniform, and the air tightness and the temperature uniformity are ensured.
The rib forming die 3 is arranged in a block mode according to the length direction of the control surface, as shown in fig. 5, the rib forming die 3 can be arranged into a combined die structure of three blocks of an upper rib block 3-1, a middle rib block 3-2 and a lower rib block 3-3, wherein the upper rib block 3-1 is arranged between the upper rib 1-2 and the middle rib 1-31, the middle rib block 3-2 is arranged between the middle rib 1-31 and the middle rib 1-32, the lower rib block 3-3 is arranged between the middle rib 1-32 and the lower rib 1-4, the three blocks can be freely split for disassembling and demolding, the die closing gaps among the three blocks are respectively not more than 0.1mm, a rib positioning piece 31 is arranged between the rib forming die 3 and the lower main body die 2 for positioning and locking, a rib demolding die 32 is arranged for demolding ejection, and the positioning tolerance between the rib forming die 3 and the lower main body die 2 is +/-0.1 mm. The rib sub-block 3-1 and the middle rib sub-block 3-2 are used as references to be positioned and combined with the lower main body die 2, then the beam forming die 4 and the lower rib sub-block 3-3 are sequentially clamped and positioned, finally the left die 5 and the right die 6 are clamped and positioned, and then the stripper plate 7 and the gusset plate 8 are installed and locked to realize the pressurization in the length direction.
The middle rib segment 3-2 is sub-modular.
As shown in figure 5, a drill plate 9 is arranged on an upper partition 21-1, an upper rib partition 3-1 and a beam forming die 4 and is used for positioning a composite frame assembly in joint bonding with a skin, a die opening plate and a drawing screw 41 connected with the end part of the beam forming die 4 are arranged on a lower main body die 2 according to the large end of a control surface so as to take out the beam forming die during demoulding, and a lifting lug 10 is arranged on the lower main body die 2 and is used for transferring a forming tool.
The molding surface manufacturing tolerance of the molding tool is +/-0.1 mm, and the surface roughness of the related working surface is Ra0.8. Score line 11 relates to the net-size edge line, sub-layup edge line, hole line, and hole center cross line of the scored part, the sub-layup line (cladding) is scored in the non-working face area, and the non-working face area is scored with the part layup fiducial line. And detecting reference holes are formed in the non-working surface area around the forming tool, and practical coordinate values are carved nearby for detecting the molded surface after the forming tool is manufactured. And the upper main body die and the lower main body die are provided with glue guide grooves for discharging redundant resin in the curing process. The forming tool is provided with a target hole matched with a laser projector, and eight laser positioning holes are formed.
The forming tool can complete co-curing and then co-bonding, and the detachable die can accurately position a plurality of ribs and beams, can be detached for demolding, and is favorable for improving the quality of products.

Claims (6)

1.一种飞机复材舵面的共固化再共胶接成型工装，其特征在于：包括相对布设的上主体模(1)和下主体模(2)，上主体模(1)上根据舵面上表面设置上蒙皮成型模，下主体模(2)上根据舵面下表面设置下蒙皮成型模，下蒙皮成型模上方设置肋成型模(3)，下蒙皮成型模侧方设置梁成型模(4)，下蒙皮成型模左端根据舵面左表面设置左模(5)，下蒙皮成型模右端根据舵面右表面设置右模(6)，左模(5)左侧设置脱模板(7)安装在下主体模(2)上，右模(6)右侧设置加力板(8)安装在下主体模(2)上，上主体模(1)与下主体模(2)之间设置定位导柱合模；1. A co-curing and co-bonding molding fixture for aircraft composite control surfaces, characterized in that: it includes an upper main mold (1) and a lower main mold (2) arranged opposite to each other, an upper skin forming mold is provided on the upper main mold (1) according to the upper surface of the control surface, a lower skin forming mold is provided on the lower main mold (2) according to the lower surface of the control surface, a rib forming mold (3) is provided above the lower skin forming mold, a beam forming mold (4) is provided on the side of the lower skin forming mold, a left mold (5) is provided at the left end of the lower skin forming mold according to the left surface of the control surface, a right mold (6) is provided at the right end of the lower skin forming mold according to the right surface of the control surface, a release template (7) is provided on the left side of the left mold (5) and installed on the lower main mold (2), a force plate (8) is provided on the right side of the right mold (6) and installed on the lower main mold (2), and a positioning guide post is provided between the upper main mold (1) and the lower main mold (2) for mold closing; 共固化制造复材框架组件时，取用上主体模(1)、下主体模(2)、肋成型模(3)、梁成型模(4)、左模(5)、右模(6)、脱模板(7)、加力板(8)，并且在肋成型模(3)与下主体模(2)之间以肋定位件(31)连接，肋成型模(3)与下主体模(2)之间设置肋脱模件(32)；共胶接制造复材舵面组件时，取用上主体模(1)、下主体模(2)、上蒙皮成型模、下蒙皮成型模、肋成型模(3)、梁成型模(4)、左模(5)、右模(6)、脱模板(7)、加力板(8)。When co-curing composite frame components, the upper main mold (1), lower main mold (2), rib forming mold (3), beam forming mold (4), left mold (5), right mold (6), demolding mold (7), and force plate (8) are used. The rib forming mold (3) and the lower main mold (2) are connected by a rib positioning piece (31), and a rib demolding piece (32) is set between the rib forming mold (3) and the lower main mold (2). When co-bonding composite rudder surface components, the upper main mold (1), lower main mold (2), upper skin forming mold, lower skin forming mold, rib forming mold (3), beam forming mold (4), left mold (5), right mold (6), demolding mold (7), and force plate (8) are used. 2.根据权利要求1所述的一种飞机复材舵面的共固化再共胶接成型工装，其特征在于：上蒙皮成型模、下蒙皮成型模均设置为上中下三个分块，舵面上表面、舵面下表面设置为中分块，上中下三个分块之间的合模间隙分别为不超过0.1mm，合模接茬分别为不超过0.1mm。2. The co-curing and co-bonding molding tooling for aircraft composite control surfaces according to claim 1, characterized in that: the upper skin molding mold and the lower skin molding mold are both set as three sections, upper, middle and lower, the upper surface of the control surface and the lower surface of the control surface are set as the middle section, the mold closing gap between the upper, middle and lower sections is not more than 0.1 mm, and the mold closing joint is not more than 0.1 mm. 3.根据权利要求1所述的一种飞机复材舵面的共固化再共胶接成型工装，其特征在于：上主体模(1)与下主体模(2)之间的合模间隙为不超过0.2mm。3. The co-curing and co-bonding molding tooling for aircraft composite control surfaces according to claim 1, characterized in that: the mold closing gap between the upper main mold (1) and the lower main mold (2) is no more than 0.2 mm. 4.根据权利要求1所述的一种飞机复材舵面的共固化再共胶接成型工装，其特征在于：肋成型模(3)按舵面长度方向设置为分块式，分块之间的合模间隙分别为不超过0.1mm，肋成型模(3)与下主体模(2)之间的定位公差为±0.1mm。4. The co-curing and co-bonding molding tooling for aircraft composite control surfaces according to claim 1, characterized in that: the rib forming mold (3) is set as a block type according to the length direction of the control surface, the mold gap between the blocks is not more than 0.1mm, and the positioning tolerance between the rib forming mold (3) and the lower main body mold (2) is ±0.1mm. 5.根据权利要求1所述的一种飞机复材舵面的共固化再共胶接成型工装，其特征在于：共胶接制造复材舵面组件时，下蒙皮成型模、肋成型模(3)、梁成型模(4)上设置钻模板(9)。5. The co-curing and co-bonding molding tooling for aircraft composite control surfaces according to claim 1, characterized in that: when co-bonding to manufacture composite control surface components, a drill template (9) is provided on the lower skin forming mold, the rib forming mold (3), and the beam forming mold (4). 6.根据权利要求1所述的一种飞机复材舵面的共固化再共胶接成型工装，其特征在于：根据舵面大头端，在下主体模(2)上设置与梁成型模(4)端部连接的启模板及拉拔螺杆(41)。6. The co-curing and co-bonding molding tooling for aircraft composite control surfaces according to claim 1, characterized in that: according to the large end of the control surface, a mold opening template and a pull-out screw (41) connected to the end of the beam forming mold (4) are provided on the lower main body mold (2).
CN202423239111.6U 2024-12-27 2024-12-27 A tooling for co-curing and co-bonding aircraft composite control surfaces Active CN223701782U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202423239111.6U CN223701782U (en) 2024-12-27 2024-12-27 A tooling for co-curing and co-bonding aircraft composite control surfaces

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202423239111.6U CN223701782U (en) 2024-12-27 2024-12-27 A tooling for co-curing and co-bonding aircraft composite control surfaces

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Publication Number Publication Date
CN223701782U true CN223701782U (en) 2025-12-23

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