技术领域technical field
本发明涉及异质材料连接结构制造技术，尤其是涉及一种复合材料与金属连接结构的制造方法。The invention relates to the manufacturing technology of heterogeneous material connecting structure, in particular to a manufacturing method of composite material and metal connecting structure.
背景技术Background technique
相比传统的金属材料，纤维增强复合材料具有高比强、高比模、各向异性、耐疲劳、耐腐蚀、性能可设计和多功能性等优势，其应用对促进航空航天装备的轻量化和高性能化具有至关重要的作用。复合材料的广泛应用不可避免会遇到复合材料与金属这两种异质材料的连接问题，如在飞机结构上大量存在的井字梁接头、桁条等金属件与复合材料蒙皮之间的连接。Compared with traditional metal materials, fiber-reinforced composite materials have the advantages of high specific strength, high specific modulus, anisotropy, fatigue resistance, corrosion resistance, performance can be designed and multi-functionality, and its application is very important to promote the lightweight of aerospace equipment and high performance play a vital role. The wide application of composite materials will inevitably encounter the connection problem of two heterogeneous materials, composite materials and metals, such as the connection between metal parts such as well-shaped beam joints and stringers and composite skins that exist in a large number of aircraft structures. connect.
现有的该连接结构的制造方法，在小型结构上应用时，可以利用数控机床进行定位钻孔。但应用到大型结构时，钻孔无法在数控机床完成。为保证孔的精确定位，需要开发适用于大型结构的钻孔方法。此外由于孔很小且需要保证被连接件的相对位置，传统的利用已固化的胶粘膜先固定位置再打孔的方法容易导致钻头折断(钻头直径低于1毫米)。因此，需要开发一种能够解决现有连接工艺所存在问题的新方法。When the existing manufacturing method of the connection structure is applied to a small structure, a numerical control machine tool can be used for positioning drilling. But when applied to large structures, drilling cannot be done on CNC machines. To ensure precise positioning of the holes, drilling methods suitable for large structures need to be developed. In addition, because the hole is very small and the relative position of the connected parts needs to be guaranteed, the traditional method of using the cured adhesive film to fix the position and then punch the hole is likely to cause the drill bit to break (the drill bit diameter is less than 1 mm). Therefore, it is necessary to develop a new method capable of solving the problems existing in the existing joining process.
发明内容Contents of the invention
本发明的目的就是为了克服上述现有技术存在的缺陷而提供一种复合材料与金属连接结构的制造方法，本发明方法既能保证大型连接件孔间的精确定位，又解决了在已固化胶膜上打孔钻头易断等问题。The purpose of the present invention is to provide a method for manufacturing a composite material and metal connection structure in order to overcome the above-mentioned defects in the prior art. The drilling bit on the film is easy to break and other problems.
本发明的目的可以通过以下技术方案来实现：The purpose of the present invention can be achieved through the following technical solutions:
一种复合材料与金属连接结构的制造方法，包括以下步骤：A method for manufacturing a composite material and metal connection structure, comprising the following steps:
(1)表面处理：对金属件与复合材料件搭接区域表面进行丙酮清洗、干燥、打磨、再清洗、再干燥的处理，尤其是金属与复合材料搭接区域；(1) Surface treatment: Acetone cleaning, drying, grinding, re-cleaning, and re-drying are performed on the surface of the overlapping area between the metal part and the composite material part, especially the overlapping area between the metal part and the composite material;
(2)铺胶：在经表面处理过的金属件与复合材料件搭接区域铺胶，使得金属件与复合材料件通过质检的胶粘膜实现搭接区域的预定位；(2) Laying glue: Laying glue on the overlapping area of the metal parts and composite material parts after surface treatment, so that the adhesive film of the metal parts and composite material parts passing the quality inspection realizes the pre-positioning of the overlapping area;
(3)搭接区域定位打孔：利用定位打孔夹具在金属件与复合材料件的搭接区域进行可重复定位钻孔；(3) Positioning and drilling in the overlapping area: use the positioning and drilling fixture to perform repeatable positioning drilling in the overlapping area between the metal part and the composite material part;
(4)插入涂有胶粘剂的细针：首先对细针进行表面处理，然后在细针表面和贯穿于金属件与复合材料件的孔中均匀涂抹胶粘剂，之后将涂有胶粘剂的细针插入孔中；(4) Inserting the fine needles coated with adhesive: firstly, surface-treat the fine needles, then apply the adhesive evenly on the surface of the fine needles and in the holes penetrating through metal parts and composite materials, and then insert the fine needles coated with adhesive into the holes middle;
(5)加温加压固化：在高温环境下保持一定时长，固化过程中要保持金属件与复合材料件之间的压力，然后温度自然降至室温，得到复合材料与金属连接结构。(5) Heating and pressurization curing: Keep it in a high temperature environment for a certain period of time. During the curing process, the pressure between the metal part and the composite material part should be maintained, and then the temperature will naturally drop to room temperature to obtain a composite material and metal connection structure.
贯穿于金属件的孔与贯穿于复合材料件的孔位置重合。The position of the hole penetrating through the metal part coincides with the position of the hole penetrating through the composite material part.
所述复合材料件的材质为已固化碳纤维增强复合材料。The composite material part is made of cured carbon fiber reinforced composite material.
胶粘区域包括金属件与复合材料件的贴合区域，以及细针与被连接件上孔的贴合区域。The adhesive area includes the lamination area of the metal part and the composite material part, and the lamination area of the thin needle and the hole on the connected part.
步骤(3)中所述的定位打孔夹具包含上夹具与下夹具，上夹具下侧形成置放复合材料件的腔体，下夹具上侧形成置放金属件的腔体，在下夹具置放金属件的腔体下侧为碎屑槽，置放复合材料件的腔体一端闭合，另一端为复合材料件延伸出去的开口，置放金属件的腔体一端闭合，另一端为金属件延伸出去的开口，所述的上夹具与下夹具的端部设置紧固螺栓孔，所述的上夹具上设置有导向孔，使用时，将复合材料件放置于上夹具内，金属件放置于下夹具内，在两侧紧固螺栓孔中通过紧固螺栓夹紧固定后，钻头通过上夹具上的导向孔对金属件与复合材料件搭接区域进行打孔。The positioning and punching jig described in step (3) includes an upper jig and a lower jig, the lower side of the upper jig forms a cavity for placing composite material parts, and the upper side of the lower jig forms a cavity for placing metal parts. The lower side of the cavity of the metal part is a debris groove, one end of the cavity for placing the composite material part is closed, and the other end is an opening from which the composite material part extends, one end of the cavity for placing the metal part is closed, and the other end is extended for the metal part Out of the opening, the ends of the upper and lower clamps are provided with fastening bolt holes, and the upper clamp is provided with guide holes. When in use, the composite material parts are placed in the upper clamp, and the metal parts are placed in the lower clamp. In the fixture, after being clamped and fixed by the fastening bolts in the fastening bolt holes on both sides, the drill bit drills holes in the overlapping area of the metal part and the composite material part through the guide hole on the upper fixture.
上夹具上所述的导向孔直径为0.5-1.5mm之间，导向孔之间互相平行，导向孔可以垂直分布也可以成一定角度分布。The diameter of the guide holes on the upper fixture is between 0.5-1.5mm, the guide holes are parallel to each other, and the guide holes can be distributed vertically or at a certain angle.
步骤(4)中所述的细针可以为碳纤维束或金属细针，其两端与被连接的复合材料件与金属件表面平齐。The fine needles described in step (4) may be carbon fiber bundles or metal fine needles, and the two ends thereof are flush with the surface of the composite material part and the metal part to be connected.
步骤(4)中将涂有胶粘剂的细针插入孔中的方法可以为手工操作，也可以通过衬套导引，空气压入等半自动化方式将细针嵌入孔中。The method of inserting the thin needle coated with adhesive into the hole in step (4) can be manually operated, or can be inserted into the hole through semi-automatic methods such as bushing guidance and air pressing.
步骤(5)中所述的固化方法由胶粘剂的种类决定，连接结构可以在室温下完成固化，也可以采用电热毯或微波加热等局部加热方法完成固化，还可以在温度箱中完成固化。The curing method described in step (5) is determined by the type of adhesive. The connection structure can be cured at room temperature, or can be cured by local heating methods such as electric blanket or microwave heating, or can be cured in a temperature box.
步骤(5)中所述固化过程中要保持一定压力，可以用紧固螺栓实现，也可以用真空袋压缩实现。A certain pressure should be maintained during the curing process described in step (5), which can be achieved by fastening bolts or compressed by vacuum bags.
与现有技术相比，本发明具有以下优点及有益效果：Compared with the prior art, the present invention has the following advantages and beneficial effects:
本发明采用定位打孔夹具进行可重复定位钻孔，克服了大型结构上对连接件打孔时定位不准的问题。此外，本发明在胶膜未固化前利用定位打孔夹具进行打孔，解决了胶膜固化后打孔由于胶层阻挡导致钻头易折断的问题。通过该方法制造的连接件有效解决机械连接孔边应力集中、重量大等缺点，以及胶接分散性大、可靠性低等缺点。而且通过本发明得到的连接结构质量轻，提高复合材料与金属连接结构的承载能力和可靠性，并降低连接结构破坏的突发性。而且本发明能够适用于大型结构连接件，工艺简单，成本低，有较强的推广性。The invention adopts a positioning punching jig to carry out repeatable positioning drilling, which overcomes the problem of inaccurate positioning when punching connectors on large structures. In addition, the present invention uses a positioning punching jig to punch holes before the glue film is cured, which solves the problem that the drill bit is easily broken due to the blocking of the glue layer after the glue film is cured. The connector manufactured by the method effectively solves the disadvantages of stress concentration at the edge of the mechanical connection hole, heavy weight, etc., as well as the disadvantages of large adhesive dispersion and low reliability. Moreover, the connection structure obtained by the invention is light in weight, improves the bearing capacity and reliability of the connection structure between the composite material and the metal, and reduces the suddenness of damage of the connection structure. Moreover, the present invention can be applied to large-scale structural connectors, has simple process, low cost and strong popularization.
附图说明Description of drawings
图1是本发明制造方法的流程图；Fig. 1 is the flow chart of manufacturing method of the present invention;
图2是本发明所针对的复合材料与金属连接结构示意图；Fig. 2 is a schematic diagram of the composite material and metal connection structure aimed at by the present invention;
图3是本发明的可重复定位钻孔夹具示意图；Fig. 3 is a schematic diagram of the repositionable drilling jig of the present invention;
图4是本发明的试验件进行定位钻孔加工示意图。Fig. 4 is a schematic diagram of the positioning drilling process of the test piece of the present invention.
图中，1是复合材料件，2是细针，3是胶粘膜，4是金属件，5是上夹具，6是下夹具，7是紧固螺栓孔，8是碎屑槽，9是导向孔。In the figure, 1 is a composite material part, 2 is a thin needle, 3 is an adhesive film, 4 is a metal part, 5 is an upper clamp, 6 is a lower clamp, 7 is a fastening bolt hole, 8 is a debris groove, and 9 is a guide hole.
具体实施方式detailed description
下面结合附图和具体实施例对本发明进行详细说明。The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.
实施例Example
一种复合材料与金属连接结构的制造方法，如图1所示，包括以下步骤：A method for manufacturing a composite material and metal connection structure, as shown in Figure 1, comprises the following steps:
(1)原材料准备：复合材料件和金属件为165mm×100mm×3mm各一块，HysolEA9696中温固化胶膜，AB胶，直径为1mm，长度为6mm的不锈钢细针。(1) Raw material preparation: Composite material parts and metal parts are 165mm×100mm×3mm each, HysolEA9696 medium temperature curing adhesive film, AB glue, stainless steel fine needles with a diameter of 1mm and a length of 6mm.
(2)表面处理：对金属件与复合材料件搭接区域表面进行丙酮擦拭，等干燥后先用500目粗砂纸打磨表面，随后再用2000目细砂纸打磨表面，然后再次用丙酮清洗，放置在通风处等待自然干燥；(2) Surface treatment: Wipe the surface of the overlapping area between the metal part and the composite material part with acetone. After drying, first polish the surface with 500-mesh coarse sandpaper, then use 2000-mesh fine sandpaper to polish the surface, and then clean it with acetone again. Wait for natural drying in a ventilated place;
(3)铺胶：在经表面处理过的金属件与复合材料件搭接区域铺Hysol EA9696胶粘膜，在常温(未固化)下加一定压力并放置30分钟，使得金属件与复合材料件通过质检的胶粘膜实现搭接区域的预定位；(3) Adhesive laying: Lay Hysol EA9696 adhesive film on the overlapping area of the metal parts and composite material parts after surface treatment, apply a certain pressure at room temperature (uncured) and place it for 30 minutes, so that the metal parts and composite material parts pass through The quality-checked adhesive film realizes the pre-positioning of the overlapping area;
(4)搭接区域定位打孔：利用定位打孔夹具在金属件与复合材料件的搭接区域进行可重复定位钻孔；(4) Positioning and drilling in the overlapping area: use the positioning and drilling fixture to perform repeatable positioning drilling in the overlapping area between the metal part and the composite material part;
(5)插入涂有胶粘剂的细针：首先对细针进行表面处理，打磨、清洗、干燥，然后在细针表面和贯穿于金属件与复合材料件的孔中均匀涂抹胶粘剂，之后将涂有胶粘剂的细针插入孔中；(5) Inserting the fine needles coated with adhesive: firstly, the fine needles are surface treated, polished, cleaned, and dried, and then the adhesive is evenly applied on the surface of the fine needles and in the holes penetrating through the metal parts and composite material parts, and then coated with A thin needle of adhesive is inserted into the hole;
(6)加温加压固化：将打好孔的试件和夹具一起放入120℃的温度箱中保持60分钟，固化过程中要保持粘接件之间的压力(200kPa)，关闭温度箱，将连接件温度自然降至室温。(6) Heating and pressure curing: put the drilled specimen and the fixture together in a temperature box at 120°C for 60 minutes. During the curing process, keep the pressure between the bonding parts (200kPa), and close the temperature box. , lower the temperature of the connector to room temperature naturally.
(7)分剪与检验(7) Cutting and inspection
将固化后的整个连接件分剪成宽度为25mm的5个连接件，之后进行拉伸试验对每个连接件进行力学性能的测试，经测试本实施例所得复合材料与金属连接结构质量轻，克服了常规机械连接导致的孔边应力集中问题，提高了复合材料与金属连接结构的承载能力和可靠性，并降低连接结构破坏的突发性。而且本发明能够适用于大型结构连接件，工艺简单，成本低，有较强的推广性。The cured whole connector is cut into 5 connectors with a width of 25mm, and then a tensile test is performed to test the mechanical properties of each connector. After testing, the composite material and metal connection structure obtained in this embodiment are light in weight, It overcomes the problem of stress concentration at the edge of the hole caused by conventional mechanical connections, improves the bearing capacity and reliability of the connection structure between composite materials and metals, and reduces the suddenness of damage to the connection structure. Moreover, the present invention can be applied to large-scale structural connectors, has simple process, low cost and strong popularization.
如图2所示本实施例的复合材料与金属连接结构包括：带有通孔的复合材料件1，涂有胶粘剂的细针2，位于贴合面的胶粘膜3，带有通孔的金属件4。As shown in Figure 2, the composite material and metal connection structure of this embodiment includes: a composite material piece 1 with a through hole, a thin needle 2 coated with an adhesive, an adhesive film 3 positioned on the bonding surface, and a metal material with a through hole. piece 4.
其中，贯穿于金属件的孔与贯穿于复合材料件的孔位置重合。Wherein, the position of the hole penetrating through the metal part coincides with the position of the hole penetrating through the composite material part.
本实施例中，复合材料件的材质为已固化碳纤维增强复合材料。In this embodiment, the material of the composite material is a cured carbon fiber reinforced composite material.
本实施例中，胶粘区域包括金属件与复合材料件的贴合区域，以及细针与被连接件上孔的贴合区域。In this embodiment, the adhesive area includes the lamination area of the metal part and the composite material part, and the lamination area of the thin needle and the hole on the connected part.
如图3、图4所示，步骤(3)中定位打孔夹具包含上夹具5与下夹具6，上夹具5下侧形成置放复合材料件的腔体，下夹具6上侧形成置放金属件的腔体，在下夹具6置放金属件的腔体下侧为碎屑槽8，置放复合材料件的腔体一端闭合，另一端为复合材料件延伸出去的开口，置放金属件的腔体一端闭合，另一端为金属件延伸出去的开口，上夹具5与下夹具6的端部设置紧固螺栓孔7，上夹具5上设置有导向孔9，使用时，将复合材料件1放置于上夹具5内，金属件4放置于下夹具6内，在两侧紧固螺栓孔7中通过紧固螺栓夹紧固定后，钻头通过上夹具5上的导向孔9对复合材料件1与金属件4搭接区域进行打孔。参考ASTM D1002-10标准，为保证试验件的一致性，降低试验结果的分散性，在专有夹具上分布5组孔，每组分布着5*3共15个孔。As shown in Figure 3 and Figure 4, the positioning punching jig in step (3) includes an upper jig 5 and a lower jig 6, the lower side of the upper jig 5 forms a cavity for placing composite material parts, and the upper side of the lower jig 6 forms a cavity for placing The cavity of the metal part is a debris groove 8 on the lower side of the cavity where the metal part is placed in the lower fixture 6. One end of the cavity for placing the composite material part is closed, and the other end is an opening through which the composite material part extends, and the metal part is placed One end of the cavity is closed, and the other end is an opening through which the metal part extends. Fastening bolt holes 7 are provided at the ends of the upper fixture 5 and the lower fixture 6, and guide holes 9 are provided on the upper fixture 5. When in use, the composite material parts 1 is placed in the upper fixture 5, and the metal part 4 is placed in the lower fixture 6. After being clamped and fixed by the fastening bolts in the fastening bolt holes 7 on both sides, the drill bit passes through the guide hole 9 on the upper fixture 5 to pair the composite material parts 1 and the metal part 4 overlap area to punch holes. Referring to the ASTM D1002-10 standard, in order to ensure the consistency of the test pieces and reduce the dispersion of the test results, 5 groups of holes are distributed on the proprietary fixture, and each group is distributed with 5*3 total of 15 holes.
上夹具8上导向孔9直径为0.5-1.5mm之间，导向孔9之间互相平行，导向孔可以垂直分布也可以成一定角度分布。The diameter of the guide holes 9 on the upper fixture 8 is between 0.5-1.5mm, and the guide holes 9 are parallel to each other. The guide holes can be distributed vertically or at a certain angle.
步骤(4)中细针可以为碳纤维束或金属细针，其两端与被连接的复合材料件与金属件表面平齐。The fine needles in step (4) can be carbon fiber bundles or metal fine needles, and the two ends of the needles are flush with the surfaces of the connected composite material parts and metal parts.
步骤(4)中将涂有胶粘剂的细针插入孔中的方法可以为手工操作，也可以通过衬套导引，空气压入等半自动化方式将细针嵌入孔中。The method of inserting the thin needle coated with adhesive into the hole in step (4) can be manually operated, or can be inserted into the hole through semi-automatic methods such as bushing guidance and air pressing.
步骤(5)中固化方法由胶粘剂的种类决定，连接结构可以在室温下完成固化，也可以采用电热毯或微波加热等局部加热方法完成固化，还可以在温度箱中完成固化。The curing method in step (5) is determined by the type of adhesive. The connection structure can be cured at room temperature, or can be cured by local heating methods such as electric blanket or microwave heating, or can be cured in a temperature box.
步骤(5)中所述固化过程中要保持一定压力，可以用紧固螺栓实现，也可以用真空袋压缩实现。A certain pressure should be maintained during the curing process described in step (5), which can be achieved by fastening bolts or compressed by vacuum bags.
上述的对实施例的描述是为便于该技术领域的普通技术人员能理解和使用发明。熟悉本领域技术的人员显然可以容易地对这些实施例做出各种修改，并把在此说明的一般原理应用到其他实施例中而不必经过创造性的劳动。因此，本发明不限于上述实施例，本领域技术人员根据本发明的揭示，不脱离本发明范畴所做出的改进和修改都应该在本发明的保护范围之内。The above descriptions of the embodiments are for those of ordinary skill in the art to understand and use the invention. It is obvious that those skilled in the art can easily make various modifications to these embodiments, and apply the general principles described here to other embodiments without creative effort. Therefore, the present invention is not limited to the above-mentioned embodiments. Improvements and modifications made by those skilled in the art according to the disclosure of the present invention without departing from the scope of the present invention should fall within the protection scope of the present invention.
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710048305.3ACN106827560A (en) | 2017-01-20 | 2017-01-20 | A kind of manufacture method of composite and metal connecting structure |
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710048305.3ACN106827560A (en) | 2017-01-20 | 2017-01-20 | A kind of manufacture method of composite and metal connecting structure |
| Publication Number | Publication Date |
|---|---|
| CN106827560Atrue CN106827560A (en) | 2017-06-13 |
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710048305.3APendingCN106827560A (en) | 2017-01-20 | 2017-01-20 | A kind of manufacture method of composite and metal connecting structure |
| Country | Link |
|---|---|
| CN (1) | CN106827560A (en) |
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110015390A (en)* | 2019-05-07 | 2019-07-16 | 珠海市琛龙船厂有限公司 | A connection structure of metal parts and glass fiber reinforced plastic and hull |
| CN110027294A (en)* | 2019-03-13 | 2019-07-19 | 成都飞机工业（集团）有限责任公司 | A kind of composite panel adhering method |
| CN110561765A (en)* | 2019-07-26 | 2019-12-13 | 中国航空工业集团公司济南特种结构研究所 | Connecting method for large-size composite material parts |
| CN112114413A (en)* | 2020-09-30 | 2020-12-22 | 中山市光大光学仪器有限公司 | Positioning jig for central pinhole-shaped cemented lens |
| CN112180533A (en)* | 2020-10-08 | 2021-01-05 | 中山市光大光学仪器有限公司 | Method for processing central pinhole-shaped cemented lens |
| CN113334781A (en)* | 2021-06-30 | 2021-09-03 | 中国航发动力股份有限公司 | Arc-shaped composite material gluing method for inner wall of fan casing |
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5935475A (en)* | 1996-06-06 | 1999-08-10 | The Boeing Company | Susceptor integration into reinforced thermoplastic composites |
| EP1163992A2 (en)* | 2000-06-15 | 2001-12-19 | Bayer Ag | Plastic-metal composite member and method for its manufacturing |
| CN202239782U (en)* | 2011-08-01 | 2012-05-30 | 安徽华东光电技术研究所 | Drilling fixture for machining channel pores of coupled cavity multi-beam travelling wave tube |
| CN103925267A (en)* | 2014-03-19 | 2014-07-16 | 刘龙权 | Composite material and metal connection structure and forming method thereof |
| CN104832507A (en)* | 2015-03-24 | 2015-08-12 | 南京航空航天大学 | Composite-material plate joint |
| CN105172317A (en)* | 2015-09-25 | 2015-12-23 | 刘龙权 | Solidified composite and enhancing method of repairing structure and connecting structure of solidified composite |
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5935475A (en)* | 1996-06-06 | 1999-08-10 | The Boeing Company | Susceptor integration into reinforced thermoplastic composites |
| EP1163992A2 (en)* | 2000-06-15 | 2001-12-19 | Bayer Ag | Plastic-metal composite member and method for its manufacturing |
| CN202239782U (en)* | 2011-08-01 | 2012-05-30 | 安徽华东光电技术研究所 | Drilling fixture for machining channel pores of coupled cavity multi-beam travelling wave tube |
| CN103925267A (en)* | 2014-03-19 | 2014-07-16 | 刘龙权 | Composite material and metal connection structure and forming method thereof |
| CN104832507A (en)* | 2015-03-24 | 2015-08-12 | 南京航空航天大学 | Composite-material plate joint |
| CN105172317A (en)* | 2015-09-25 | 2015-12-23 | 刘龙权 | Solidified composite and enhancing method of repairing structure and connecting structure of solidified composite |
| Title |
|---|
| 李蔚等: "《机械制造基础》", 29 February 2012, 西北工业大学* |
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110027294A (en)* | 2019-03-13 | 2019-07-19 | 成都飞机工业（集团）有限责任公司 | A kind of composite panel adhering method |
| CN110015390A (en)* | 2019-05-07 | 2019-07-16 | 珠海市琛龙船厂有限公司 | A connection structure of metal parts and glass fiber reinforced plastic and hull |
| WO2020224329A1 (en)* | 2019-05-07 | 2020-11-12 | 珠海市琛龙船厂有限公司 | Connecting structure of metal member and fiberglass, and watercraft body |
| CN110561765A (en)* | 2019-07-26 | 2019-12-13 | 中国航空工业集团公司济南特种结构研究所 | Connecting method for large-size composite material parts |
| CN112114413A (en)* | 2020-09-30 | 2020-12-22 | 中山市光大光学仪器有限公司 | Positioning jig for central pinhole-shaped cemented lens |
| CN112180533A (en)* | 2020-10-08 | 2021-01-05 | 中山市光大光学仪器有限公司 | Method for processing central pinhole-shaped cemented lens |
| CN113334781A (en)* | 2021-06-30 | 2021-09-03 | 中国航发动力股份有限公司 | Arc-shaped composite material gluing method for inner wall of fan casing |
| Publication | Publication Date | Title |
|---|---|---|
| CN106827560A (en) | A kind of manufacture method of composite and metal connecting structure | |
| CN106226155B (en) | A composite material sheet in-plane shear test fixture and test method | |
| CN108152093B (en) | Method of preparing elongated laminate samples for interlaminar adhesion testing | |
| Matta et al. | Prediction of mechanical behaviour of adhesively bonded CFRP scarf jointed specimen under tensile loading using localised DIC and CZM | |
| CN104880351B (en) | A kind of unidirectional ceramic matric composite flat test piece and preparation method thereof | |
| US20110067499A1 (en) | Method and Template for Producing a Tensile Test Coupon | |
| CN107621408A (en) | A method and device for evaluating and testing the GIC of the I-mode interlaminar fracture toughness of fiber metal laminates | |
| CN108535101A (en) | A kind of measurement method of composite laminated plate interlaminal tensile strength | |
| Beylergil et al. | Experimental and numerical analysis of single lap composite joints with inter-adherend fibers | |
| CN114062118B (en) | A tensile, compressive and shearing integrated fiber laminate experimental fixture and its use method | |
| CN106645277A (en) | Tester for testing fiber axial heat conduction performance and production method thereof | |
| Rao et al. | Effect of geometric parameters of finger joint profile on ultimate tensile strength of single finger-joined boards | |
| DE60212996D1 (en) | METHOD FOR MANUFACTURING AND INDIRECTLY TESTING A COMPOSITE LAYER ON A FLIGHT BODY COMPONENT | |
| CN108318317A (en) | A kind of high throughput prepares the device and method of micro- key unsticking experimental sample | |
| Campilho | Repair of composite and wood structures | |
| CN109253903A (en) | A kind of composite material technique for sticking that adhesive thickness is controllable | |
| CN102539317A (en) | Bonding strength testing device | |
| CN108760437B (en) | Sample preparation method for tensile shear strength of structural adhesive steel to steel | |
| CN106273561A (en) | A kind of repair method of composite material closed cavity body structure through hole defect | |
| US10078041B2 (en) | Flatwise material coupon | |
| CN118817505A (en) | A test method for monitoring the delamination defect growth process in composite materials under fatigue environment | |
| CN113188869A (en) | Tool for preparing composite material test sample piece and test sample piece preparation method | |
| CN209624226U (en) | A kind of irregular section composite materials testing part stretching clamp with metal joint | |
| CN204789288U (en) | Special fixture from pressure test is pulled in gluing agent | |
| Frihart | Durable wood bonding with epoxy adhesives |
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication | Application publication date:20170613 |