CN101348169A - 用于将金属整流罩粘接到机翼前缘的方法和设备 - Google Patents

用于将金属整流罩粘接到机翼前缘的方法和设备 Download PDF

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Publication number
CN101348169A
CN101348169A CNA2008102147749A CN200810214774A CN101348169A CN 101348169 A CN101348169 A CN 101348169A CN A2008102147749 A CNA2008102147749 A CN A2008102147749A CN 200810214774 A CN200810214774 A CN 200810214774A CN 101348169 A CN101348169 A CN 101348169A
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equipment
metal
temperature
fairings
main stor
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CN101348169B (zh
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P·波斯切特
T·那瓦热
B·落赛特
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Kong Kezhishengji
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Airbus Helicopters SAS
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/02—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure
    • B29C65/44—Joining a heated non plastics element to a plastics element
    • B29C65/46—Joining a heated non plastics element to a plastics element heated by induction
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/28—Leading or trailing edges attached to primary structures, e.g. forming fixed slots
    • 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
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • 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
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/4805—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the type of adhesives
    • B29C65/483—Reactive adhesives, e.g. chemically curing adhesives
    • B29C65/4835—Heat curing adhesives
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/74—Joining plastics material to non-plastics material
    • B29C66/742—Joining plastics material to non-plastics material to metals or their alloys
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    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B29C66/9141—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux by controlling or regulating the temperature, the heat or the thermal flux by controlling or regulating the temperature
    • B29C66/91441—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux by controlling or regulating the temperature, the heat or the thermal flux by controlling or regulating the temperature the temperature being non-constant over time
    • B29C66/91443—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux by controlling or regulating the temperature, the heat or the thermal flux by controlling or regulating the temperature the temperature being non-constant over time following a temperature-time profile
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/90—Measuring or controlling the joining process
    • B29C66/91—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux
    • B29C66/914—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux by controlling or regulating the temperature, the heat or the thermal flux
    • B29C66/9141—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux by controlling or regulating the temperature, the heat or the thermal flux by controlling or regulating the temperature
    • B29C66/91441—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux by controlling or regulating the temperature, the heat or the thermal flux by controlling or regulating the temperature the temperature being non-constant over time
    • B29C66/91443—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux by controlling or regulating the temperature, the heat or the thermal flux by controlling or regulating the temperature the temperature being non-constant over time following a temperature-time profile
    • B29C66/91445—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux by controlling or regulating the temperature, the heat or the thermal flux by controlling or regulating the temperature the temperature being non-constant over time following a temperature-time profile by steps
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/90—Measuring or controlling the joining process
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    • B29C66/914—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux by controlling or regulating the temperature, the heat or the thermal flux
    • B29C66/9161—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux by controlling or regulating the temperature, the heat or the thermal flux by controlling or regulating the heat or the thermal flux, i.e. the heat flux
    • B29C66/91651—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux by controlling or regulating the temperature, the heat or the thermal flux by controlling or regulating the heat or the thermal flux, i.e. the heat flux by controlling or regulating the heat generated by Joule heating or induction heating
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/90—Measuring or controlling the joining process
    • B29C66/91—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux
    • B29C66/919—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux characterised by specific temperature, heat or thermal flux values or ranges
    • B29C66/9192—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux characterised by specific temperature, heat or thermal flux values or ranges in explicit relation to another variable, e.g. temperature diagrams
    • B29C66/91951—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux characterised by specific temperature, heat or thermal flux values or ranges in explicit relation to another variable, e.g. temperature diagrams in explicit relation to time, e.g. temperature-time diagrams
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B64C27/473—Constructional features
    • C—CHEMISTRY; METALLURGY
    • C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
    • C09J—ADHESIVES; NON-MECHANICAL ASPECTS OF ADHESIVE PROCESSES IN GENERAL; ADHESIVE PROCESSES NOT PROVIDED FOR ELSEWHERE; USE OF MATERIALS AS ADHESIVES
    • C09J5/00—Adhesive processes in general; Adhesive processes not provided for elsewhere, e.g. relating to primers
    • C09J5/06—Adhesive processes in general; Adhesive processes not provided for elsewhere, e.g. relating to primers involving heating of the applied adhesive
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B6/00—Heating by electric, magnetic or electromagnetic fields
    • H05B6/02—Induction heating
    • H05B6/10—Induction heating apparatus, other than furnaces, for specific applications
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    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
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    • C—CHEMISTRY; METALLURGY
    • C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
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    • C09J2400/00—Presence of inorganic and organic materials
    • C09J2400/10—Presence of inorganic materials
    • C09J2400/16—Metal
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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
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    • Y10T156/10—Methods of surface bonding and/or assembly therefor
    • Y10T156/1089—Methods of surface bonding and/or assembly therefor of discrete laminae to single face of additional lamina

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Electromagnetism (AREA)
  • Organic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
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Abstract

本发明涉及一种用于粘接金属整流罩(6)以保护飞行器机翼(7)前缘的方法和设备(1)，所述金属整流罩(6)被设计成通过利用胶粘剂(9)粘接到所述机翼(7)上。所述粘接设备(1)值得注意的是包括刚性轭(2)，该刚性轭具有嵌入其中的用于加热所述金属整流罩(6)的感应式加热装置(30)。

Description

用于将金属整流罩粘接到机翼前缘的方法和设备
技术领域
本发明涉及一种将金属整流罩(fairing)粘接到飞行器机翼前缘(例如，旋翼飞行器的旋翼叶片)的方法和设备。
背景技术
例如，通过将U型截面的金属整流罩粘接到叶片结构上，或者采用例如EP0529917A中所述复合材料制成的整流罩，可以保护旋翼飞行器的旋翼叶片前缘免受撞击。整流罩因此不仅保护叶片前缘同时也保护叶片的直接邻近于前缘的吸入侧和压力侧部分。
当金属整流罩被撞击或甚至被侵蚀环境损坏时，为了确保能够继续适当地保护叶片，用新的金属整流罩替换旧的是较为适宜的。
此外，为了修复叶片结构，叶片前缘可以被去除也是必需的，特别是叶片是由复合材料制成并且结构表面是分层的。一旦完成修复，就需要将叶片的前缘放回原先的位置。
一种已知的设备可以利用胶粘剂将金属整流罩粘接回到叶片前缘的位置，所述胶粘剂分布于金属整流罩和叶片结构之间。
这种设备利用加热工具来传导聚合胶粘剂所需的能量，从而将金属整流罩粘接到叶片结构上，所述胶粘剂分布于金属整流罩与叶片结构之间。加热工具由分布于金属整流罩外表面的垫板(mat)组成。
垫板包含嵌入在聚硅酮层中的热阻。当通电后，热阻加热，从而使得金属整流罩被粘接至叶片结构。热阻于是通过传导加热金属整流罩，而整流罩将热量依次传递到胶粘剂，致使胶粘剂聚合。
这种设备操作合理。然而，也存在一些缺陷。
第一个缺陷就是利用电阻而导致的结果。所有被加热垫板围绕的元件均被垫板加热，也就是说，金属整流罩、胶粘剂和叶片结构同时被加热。这样导致的能量浪费并不是最优化所需的。
同样的，第二个缺陷在于边缘效应。从设备边缘传导会导致大量的热量损失，这就意味着这种设备的操作是不统一的。从而装置的某些包含金属整流罩和叶片结构的区域被加热的程度会小于其它区域，从而以能量的过度消耗而告终以便补偿损失。
第三个缺陷是由于热阻的温度上升时间导致的，温度上升的速度为1.5摄氏度每分钟(℃/min)的级别，这样的速度是非常慢的。那么加热金属整流罩的周期就会很容易达到8小时，而这样长的时间从工业上讲就是在经济方面的惩罚。
此外，由于温度上升的比较慢，机翼就要遭受长时间的温差应力，而这样则会降解机翼。
最后，制造垫板的过程是非常冗长的，并且因此是昂贵的，而这又与急切的工业需求相矛盾，如可能会不幸地发生的是，当制造者需要修理叶片时却持有较差状态下的加热垫板。
文献WO01/30116公开了一种粘接设备，该粘接设备包含用来熔化胶粘剂的感应式加热装置。然而，该粘接设备看起来很难应用到机翼前缘的金属整流罩上。
发明内容
本发明的目的因此是提供一种用于统一且快捷地将金属整流罩粘接到前缘上，同时避免上述设备的局限性的设备。
根据本发明，用来将保护性的金属整流罩粘接到机翼前缘的粘接设备，该金属整流罩借助于胶粘剂粘接到机翼上，所值得注意的是粘接设备具有刚性轭，其中嵌入用来加热金属整流罩以粘接到机翼上的感应式加热装置。
因此，感应式加热装置加热金属整流罩，而金属整流罩通过传导依次加热胶粘剂从而使胶粘剂发生聚合。更准确地说，感应式加热装置产生由大量磁感线构成的变化的磁场，并在金属整流罩的金属材料内感应产生电动势(emfs)。这些电动势然后感应产生名为漩涡电流的电流，这些电流利用焦尔效应加热金属整流罩的材料。
由于仅仅金属元件被通过感应而加热，就不会再有因为边缘效应而产生损失，也不会再有任何因为与在前缘上粘接金属整流罩无关的元件被加热而产生损失。
从而感应式加热装置可以迅速加热金属整流罩，特别是因为减少了热量的损失。另外，这种加热方式比传导式加热快很多，例如，在现有技术中所实施的方式。
此外，胶粘剂的温度也会像感应式加热装置产生的磁感线那样毫不费力地分布均匀。缺少由于边缘效应而产生的损失，保证了胶粘剂的温度会更加均匀，在这里均匀的温度对于粘接前缘整流罩是非常重要的。
作为举例，就不需要将金属整流罩加热的时间长于设定时间，因为所加热的温度是可以全面控制的。
最后，由于加热设备仅仅加热金属整流罩，而胶粘剂则是通过从整流罩的传导而加热的，加热设备就不会冒由于过度加热而损坏机翼结构的风险。
有利地，感应式加热装置布置在由热膨胀材料构成的第一和第二主层之间，例如是聚硅酮类的，当设备使用的时候第二主层与金属整流罩的形状相匹配。
粘接设备还连续地设置有不可变形的刚性轭、第一主层、感应式加热装置，然后是第二主层。
另外，用于前缘的金属整流罩按照惯例是U型截面的。因而，第一主层和第二主层也是U型截面的。第二主层与金属整流罩的外表面接触，同时金属整流罩的内表面与用来将其粘接到机翼上的胶粘剂接触。
此外，第一和第二主层是由热膨胀材料制成的。从而，当感应式加热装置加热金属整流罩时，整流罩会通过传导传递一定量的热量到第二主层。
由于其自身的特性，第二主层然后开始膨胀。由于轭是刚性的，因此其不会在第二主层的膨胀作用下变形。因此第二主层的膨胀压力就施加于金属整流罩上。
由于会有助于金属整流罩更加合适地粘接到机翼上，因此这种现象是特别重要的。
在感应式加热装置的作用下，胶粘剂发生聚合，从而使得金属整流罩粘接到机翼结构上。另外，由于第二主层的膨胀而施加在金属整流罩上的压力也会优化粘和作用。
类似地，第一主层也会在感应式加热装置的作用下膨胀，并且上述膨胀产生的压力也会叠加到设备所施加的压力中。
此外，第二主层的厚度在1mm到2mm范围内，优选的是1.5mm。令人惊讶的是，这个厚度使得感应加热最大化。
在一种变型中，本发明的设备包含有热膨胀材料制成的次级层，该次级层布置在所述刚性轭和所述第一主层之间。随后，粘接设备连续地设置有不变形的刚性轭、次级层、第一主层、感应式加热装置，然后是第二主层。
第二主层用于隔离粘接设备的轭，这样感应加热装置就不会加热轭，加热装置就会将热量主要地用来加热金属整流罩。
从而，次级层的厚度有利地在6mm到8mm的范围内。
可选地是，在所述次级层和所述第一主层之间设有金属板。
由加热装置产生的磁感线的分布使得感应式加热装置加热金属板。从而可以加热第一主层和次级层，进而使得第一主层和次级层膨胀并有助于促使粘接设备施加压力至金属整流罩上。
为了最大化地加热金属板，第一主层的厚度在1mm到2mm的范围内，优选的是1.5mm。
粘接设备产生的压力有效地促进了将金属整流罩粘接到机翼上。然而，令人惊讶的是，当这个压力超过一定极限时就会变得有害。
如果压力过大，就会有胶粘剂从金属整流罩和机翼之间的空隙中脱落的风险。
因此，本发明的设备可选地具有能量吸收装置，例如与所述轭相连的额定弹簧。
能量吸收装置应当布置在刚性轭和第一主层之间，或者是在刚性轭和次级层之间，这取决于所使用的变型。
另外，为了确保压力保持在可接受的极限内，将粘接设备与监控装置相关联是有利的，所述监控装置用来监控由设备施加在金属整流罩上的压力。
从而监控设备设有嵌入到第二主层的光纤，例如，并且被联接至监控构件。
最后，可以通过优化感应式加热装置的形状，从而避免生成会导致对金属整流罩加热不均匀的热区域。
感应式加热装置包含4组绞合线，第一和第二组分布在第一和第二主层之间，这样就可以位于机翼的吸入侧，第三和第四组分布在第一和第二主层之间，这样就可以位于金属整流罩的压力侧。
此外，第一组与第二组分离开，从而释放未加热的空隙，第三组同样与第四组分离开。
从而，由加热装置产生的磁力线均匀且全面地加热金属整流罩。
本发明同样提供了一种能够在金属整流罩和机翼之间实施迅速且无损坏粘合的粘合方法。
根据本发明，一种将保护性的金属整流罩粘接至飞机机翼前缘的方法，利用分布于金属整流罩和机翼之间的胶粘剂，和布置于金属整流罩外表面的粘接设备，所值得注意的是连续实施以下步骤：
a)借助于粘接设备感应加热金属整流罩以达到第一温度，在该第一温度下胶粘剂是液态的，从而润湿机翼和金属整流罩；
b)在第一时间段结束时，增加整流罩的温度，以达到能够使胶粘剂聚合的第二温度；
c)在第二时间段结束时，增加金属整流罩的温度以达到能够使胶粘剂完全并且均匀聚合的第三温度；以及
d)在第三时间段结束时，使所述金属整流罩的温度下降。
当被装配有能够使整流罩温度上升非常迅速的感应式加热装置时，且当使用本发明所述的装置实施时，该方法是特别有效的。
在步骤a)中，胶粘剂充分地润湿金属整流罩和机翼结构，从而保证粘接均匀。
在步骤b)中，胶粘剂开始聚合，从而使得粘接有效果。
最后，在步骤c)中，温度到达一个相对较高的温度，由于第三温度大于胶粘剂的理论聚合温度值，但是仅在一个较短的时间段内，所以会中止胶粘剂的聚合。
为了优化本方法的时间段，第一时间段在10分钟到20分钟范围内，并且第三时间段在3分钟到10分钟范围内。
类似地，第二时间段在10分钟到20分钟范围内，并达到胶粘剂完全聚合的60％到80％。
应当注意到的是，为了优化实施本方法的总的时间段，第三时间段是非常短的。为了获得如此短的时间段，第三温度值高于胶粘剂的聚合温度值是有利的。这样就使得胶粘剂在较短的时间内从液态转换为固态并完成聚合成为可能。
附图说明
本发明的优点详细地出现在下文的具体实施例的描述中，并结合附图进行说明，其中：
图1为沿本发明的一个变型截取的截面图；
图2为吸收装置的图解示意图；
图3为加热装置的最优布置的截面图；以及
图4为解释本发明步骤的曲线图。
具体实施方式
出现在两幅或者更多幅附图中的元件采用相同的附图标记。
图1示出了本发明的一个变型的截面图。
为了将金属整流罩6固定在机翼末端的前缘上，在机翼7(例如旋翼飞行器的叶片)的端部处放置胶粘剂9。
此外，为了使得胶粘剂聚合，在金属整流罩的外表面F1上设有粘接设备，其中胶粘剂在加热后可以发生化学反应聚合从而粘接到材料上。
粘接设备1包括刚性轭，该刚性轭具有安装于其中的感应式加热装置30用来加热金属整流罩6。
更准确地说，感应式加热装置嵌入到第一主层5’和第二主层5″之间，其中所述第一和第二主层由热膨胀材料(例如聚硅酮)制成。
另外，在本发明的一个变型中，粘接设备1设有由隔绝热膨胀的材料制成的次级层3和例如钛金属制成的金属板4。
因而，粘接设备1连续包括：刚性轭2；次级层；金属板4；第一主层5’；感应式加热装置30；和紧密地安装于金属整流罩6外表面F1的第二主层5″。
从而，当控制装置(图中未示出)被用来操作感应式加热装置时，金属整流罩被加热且依次加热胶粘剂而使胶粘剂聚合。
此外，感应式加热装置30同样加热金属板4。
在这样的情况下，与金属整流罩6接触的第二主层5″遭受温度升高，并且由于其材料是热膨胀的而开始膨胀。上述情况同样发生于与金属板4接触的次级层3和第一主层5’。
由于轭2的刚性足以保证其不会变形，因此热膨胀层5’、5″和3的膨胀就会从粘接设备1产生压力并压向金属整流罩6，这种压力助长金属整流罩6和机翼7端部之间的粘附作用。
为了最大化这种粘附作用，第一层5’和第二层5″的厚度处于1mm到2mm之间，优选地等于1.5mm。从而，感应式加热装置30与采用相同加热方式的受热元件之间保持最优距离，也就是说，金属整流罩6和金属板4。
相反，次级层3的厚度范围在6mm到8mm。这样，该次级层就会隔离轭2，使其不会受到感应式加热装置的加热。
此外，感应式加热装置有利地设有包含单根电线的线圈，即本领域技术人员通常所称的“绞合线”。这样的绞合线是由彼此相互绝缘的单股线组成并且按照正弦型分布在外部保护物内，每一股线周期性的占用外部保护物内的所有可能的位置。根据统计，所有的线因而受到相同的电磁约束。结果，所有的线传递相同的电流，这就意味着电线中的电流密度是相同的。
感应式加热装置因而包含具有电路30’的线圈，为了方便称之为“去程(go)”电路，该线圈被排列在刚性轭内的第一主层5’和第二主层5″之间。
另外，感应式加热装置30的线圈具有电路30’，为了方便称之为“回程(return)”电路。该回程电路30″排列在金属护套22内，所述金属护套22借助隔离层21与热量隔离。
有利地，包围感应式加热装置30的回程电路30″的金属护套22与刚性轭2间隔的距离L不小于100mm，这样回程电路就不会对由去程电路30’产生的磁场产生影响。
最后，为了控制粘接设备1的加热周期，控制装置首先作用于频率，该频率为50kHz级别，这同样应用于加热装置，其次作用于传导的电流密度，此处电流密度为4×106至6×106安培每平方米(A/m2)。
另外，监视粘接设备1施加于金属整流罩6的压力是有利的，该压力是由第一主层5’和第二主层5″和次级层3的膨胀所产生的。过高的压力会产生不利的影响，因为胶粘剂会在经受高压时蠕动，从而导致从机翼上脱落。
因此，可任选地为粘接设备提供压力监控装置(未示出)。压力监控可以通过利用连接至监控单元的光纤而获得，所述监控单元例如结合在粘接设备1的控制装置中。
光纤于是设置在粘接设备1的其中一层中，优选地设置在第二主层5″中。
施加于金属整流罩上的压力的变化导致施加在光纤上压力也发生变化，从而导致发出的光线亮度的改变。作为光线亮度的函数，控制单元推断施加的压力并传达信息到控制装置，所述控制装置例如可以在压力过大的情况下切断感应式加热装置。
类似地，参照图2，在热膨胀材料过度膨胀的情况下，可以提供固定到刚性轭2的能量吸收装置以用来吸收能量。
能量吸收装置具有额定的弹簧8，该额定弹簧8被固定到刚性轭2并且还固定到第二次级层3。如果粘接设备施加在金属整流罩6上的压力趋向于超过预定阈值时，额定弹簧8于是收缩，从而使得施加在金属整流罩上的压力保持不高于所述阈值的水平。
应当注意的是，如果所实施的本发明的变型不包括次级层3或金属板4，那么额定弹簧可以被固定到第二主层5″。
图3为示出了用于加热装置的最优布置的截面图。
感应式加热装置30的去程电路30’布置在第一和第二主层之间，其具有4组分离的绞合线，邻近的绞合线组之间分布有绝缘材料，例如聚硅酮。
随后，第一组11和第二组12分布在金属整流罩6的吸入侧。类似地，第三组13和第四组14分布在金属整流罩的压力侧。
感应式加热装置的这种特殊分布是为了避免形成热区(heat point)，所述热区将会导致粘接设备1产生不均匀加热。
另外，为了使得该设备能够适用于任意一种机翼，可以设想将其制成两个在金属整流罩前缘处用弹簧连接在一起的不同的块。
第一块包括第一组11和第二组12，而第二块拥有第三组13和第四组14。
图4示出了根据本发明粘接设备实施的方法。
在初步步骤中，操作员先将胶粘剂放在机翼7的末端上，该机翼7将在其前缘上接纳金属整流罩。
随后，操作员将金属整流罩放置在适当的位置，然后将粘接设备1排列在金属整流罩上。
这样就可以开始粘接了。
在步骤a)中，控制装置激发感应式加热装置，以使金属整流罩达到第一温度t1。然后温度迅速上升，速率在2℃/分钟至10℃/分钟的范围内。
如果假定胶粘剂是120℃级别的，也就是在120℃下发生聚合，然后需要6分钟从为20℃的环境温度t0到达约为80℃的第一温度t1。
在温度t1时，胶粘剂完全是液态的，并且能够完全润湿与其接触的表面，也就是机翼末端的表面和金属整流罩的表面，这对于获得均匀粘接来说很重要。当用来粘接在一起的表面之间的接触面区域没有任何空气气泡时，所述表面就被完全润湿，以使接触面区域仅仅包括以均匀方式分布的胶粘剂，从而可以充满用来粘接在一起的纤维。
在范围为10分钟至20分钟的第一时间段d1结束时，步骤b)开始。
控制装置以5℃/分钟至10℃/分钟的速度升高金属整流罩6的温度，从而达到能够使聚合开始的第二温度t2。
由于胶粘剂是120℃级别的，聚合开始时的第二温度约为110℃，而且第二温度取决于胶粘剂所采用的化学成分。
在范围为10分钟至20分钟的第二时间段d2结束时，胶粘剂的聚合反应达到完全聚合的60％到80％。
为了降低加热时间，在第二时间段d2结束时，控制装置为了中止聚合而启动步骤c)。当胶粘剂为120℃级别时，为了达到约为140℃的第三温度t3，于是以5℃/分钟至15℃/分钟的速率将金属整流罩的温度升高，如果需要可以高至30℃/分钟。
在步骤d)中以2℃/分钟级别的速率逐渐地降低温度之前，控制装置于是在非常短的第三时间段d3内保持该第三温度，时间为3分钟至10分钟。
因此，粘接方法是非常迅速的。另外，由于加热装置的特性，加热过程是在金属整流罩的整个区域内统一实施的。
此外，在较短的时间段d3内维持高温度t3也不会冒损坏机翼的风险。
自然地，关于本发明的实施可以适用于许多变化。尽管描述了几个实施例，但是容易理解的是不可能将所有可能的实施例都详尽地识别出来。自然，可以在未超出本发明的范围的情况下设想利用等效的装置替换所描述的装置。
特别是，第一、第二和第三温度值以及上述第一、第二和第三时间段的值均取决于所用的胶粘剂，并且它们特别应用于120℃级别的胶粘剂。
这些值取决于应用到粘接机翼前缘的胶粘剂的特性，自然可以不同于那些提及的值，而且它们并未超出本发明的范围，方法本身也是同样的。

Claims (18)

1、一种用于粘接金属整流罩(6)用来保护飞行器机翼(7)前缘的粘接设备(1)，所述金属整流罩(6)借助于胶粘剂(9)粘接到所述机翼(7)上，所述设备包括一刚性轭(2)，其中嵌有感应式加热装置(30)用于加热所述金属整流罩(6)，该设备的特征在于：所述感应式加热装置(30)布置在由热膨胀材料制成的第一和第二主层(5’、5″)之间，所述第二主层(5″)在使用所述设备(1)时与所述金属整流罩(6)的形状相匹配。
2、如权利要求1中所述的设备，其特征在于，所述第二主层(5″)的厚度在1mm到2mm的范围内。
3、如前述权利要求中任一项所述的设备，其特征在于，所述第一主层(5’)的厚度在1mm到2mm的范围内。
4、如前述权利要求中任一项所述的设备，其特征在于，包括分布在所述刚性轭(2)和所述第一主层(5’)之间且由热膨胀材料制成的次级层(3)。
5、如权利要求4中所述的设备，其特征在于，所述次级层(3)的厚度在6mm至8mm的范围内。
6、如权利要求4或5所述的设备，其特征在于，在所述次级层(3)和所述第一主层(5’)之间布置有金属板(4)。
7、如前述权利要求中任一项所述的设备，其特征在于，包括固定于所述轭(2)的能量吸收装置(8)。
8、如前述权利要求中任一项所述的设备，其特征在于，设有用于监控所述设备(1)施加于所述整流罩(6)上的压力的监控装置。
9、如权利要求8中所述的设备，其特征在于，所述监控装置设有连接到监控单元的光纤。
10、如权利要求8或9所述的设备，其特征在于，所述光纤嵌入到所述第二主层(5″)中。
11、如前述权利要求中任一项所述的设备，其特征在于，所述感应式加热装置(30)具有4组(11、12、13、14)绞合线，第一和第二组(11、12)布置在第一和第二主层(5’、5″)之间，从而位于所述整流罩(6)的吸入侧，第三和第四组(13、14)布置在第一和第二主层(5’、5″)之间，从而位于所述金属整流罩(6)的压力侧。
12、如权利要求11所述的设备，其特征在于，所述第一组(11)与所述第二组(12)分离开，从而释放未加热的空隙，所述第三组(13)同样与所述第四组(14)分离开。
13、一种粘接用于保护飞行器机翼前缘的金属整流罩(6)的方法，胶粘剂(9)分布在所述金属整流罩(6)和所述机翼(7)之间，在所述金属整流罩(6)的外表面(F1)周围布置有如权利要求1至12中任一项所述的粘接设备，该方法的特征在于包括以下步骤：
a)借助于所述粘接设备(1)感应加热所述金属整流罩(6)以达到第一温度(t1)，在该第一温度下所述胶粘剂(9)是液态的，从而润湿所述机翼(7)和所述金属整流罩(6)；
b)在第一时间段(d1)结束时，增加整流罩的温度，以达到能够使所述胶粘剂(9)聚合的第二温度(t2)；
c)在第二时间段(d2)结束时，增加所述金属整流罩(6)的温度以达到能够使聚合完全且均匀发生的第三温度(t3)；以及
d)在第三时间段(d3)结束时，使所述金属整流罩的温度下降。
14、如权利要求13所述的方法，其特征在于，所述第一时间段(d1)在10分钟到20分钟的范围内。
15、如权利要求13或权利要求14所述的方法，其特征在于，所述第二时间段(d2)在10分钟到20分钟的范围内。
16、如权利要求13至15中任一项所述的方法，其特征在于，所述第三时间段(d3)在3分钟到10分钟的范围内。
17、如权利要求13至16中任一项所述的方法，其特征在于，当所述胶粘剂(9)的聚合达到胶粘剂(9)的完全聚合的60％到80％时，所述第二时间段(d2)结束。
18、如权利要求13至17中任一项所述的方法，其特征在于，所述第三温度(t3)高于胶粘剂(9)的理论聚合温度。
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