CN103042695A - 用于在脱离压热器时进行结构物剪切粘接的方法和设备 - Google Patents

用于在脱离压热器时进行结构物剪切粘接的方法和设备 Download PDF

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Publication number
CN103042695A
CN103042695A CN2012103452266A CN201210345226A CN103042695A CN 103042695 A CN103042695 A CN 103042695A CN 2012103452266 A CN2012103452266 A CN 2012103452266A CN 201210345226 A CN201210345226 A CN 201210345226A CN 103042695 A CN103042695 A CN 103042695A
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Prior art keywords
covering
framework
bonded assembly
tail boom
translation
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CN2012103452266A
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CN103042695B (zh
Inventor
P·奥尔德罗伊德
J·D·希奇科克
R·克莱夫·菲尔斯
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Bell Helicopter Textron Inc
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Bell Helicopter Textron Inc
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    • 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
    • B29C65/18—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated tools
    • B29C65/22—Heated wire resistive ribbon, resistive band or resistive strip
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
    • B29C66/51—Joining tubular articles, profiled elements or bars; Joining single elements to tubular articles, hollow articles or bars; Joining several hollow-preforms to form hollow or tubular articles
    • B29C66/52—Joining tubular articles, bars or profiled elements
    • B29C66/522—Joining tubular articles
    • B29C66/5221—Joining tubular articles for forming coaxial connections, i.e. the tubular articles to be joined forming a zero angle relative to each other
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • 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
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    • B29C65/4835—Heat curing adhesives
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    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
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    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
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    • B29C66/13—Single flanged joints; Fin-type joints; Single hem joints; Edge joints; Interpenetrating fingered joints; Other specific particular designs of joint cross-sections not provided for in groups B29C66/11 - B29C66/12
    • B29C66/131—Single flanged joints, i.e. one of the parts to be joined being rigid and flanged in the joint area
    • 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
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/32—Measures for keeping the burr form under control; Avoiding burr formation; Shaping the burr
    • B29C66/326—Shaping the burr, e.g. by the joining tool
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
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    • B29C66/53—Joining single elements to tubular articles, hollow articles or bars
    • B29C66/532—Joining single elements to the wall of tubular articles, hollow articles or bars
    • B29C66/5324—Joining single elements to the wall of tubular articles, hollow articles or bars said single elements being substantially annular, i.e. of finite length
    • B29C66/53245—Joining single elements to the wall of tubular articles, hollow articles or bars said single elements being substantially annular, i.e. of finite length said articles being hollow
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    • B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
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    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B11/00—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding
    • F16B11/006—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding by gluing
    • 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
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
    • 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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Abstract

本发明公开了一种用于在脱离压热器时进行结构物的剪切粘接的方法和设备。本申请的剪切粘接方法能够在脱离压热器的环境中促进结构物的粘接。剪切粘接方法配置成将多个框架元件粘接到渐缩的尾梁内部。这些框架设置在卡口型工具上。粘接组件具有多个施加到每个框架的接合表面上的粘膜层。卡口型工具插入到尾梁中直到粘接组件与尾梁的内壁相接触。导热砖施加到尾梁的外部。导热砖被控制用于首先实现和维持粘接组件的粘度。在这个期间卡口工具被驱动以使得框架相对于尾梁平移，由此涂敷胶粘粘接剂并且在胶层上建立主动机械压力直到框架被定位在最终位置。导热砖接着被控制以实现和维持粘接剂处于必要的固化温度。

Description

用于在脱离压热器时进行结构物剪切粘接的方法和设备
技术领域
本申请涉及一种结构物的粘接组件。尤其是，本申请涉及在脱离压热器的环境中使用用于航空航天结构物粘性剂剪切粘接方法。
背景技术
典型地，复合结构元件的粘接需要热量和压力用于最后的固化。一种实现必要的热量和压力的方法为组件处于压热器内的同时进行抽真空。压热器使组件经受热量和压力，由此固化组件中的粘合剂。然而，结构组件中的粘合剂的压热器固化并不总是可行的。例如，组件的尺寸阻止压热器固化。进而，结构组件的几何形状会阻挡在粘接区域周围安装真空袋的通道。进而，组件中出现的热敏材料可能为压热器固化带来不便。
尽管结构组件中的粘合剂固化的发展有了重大的改进，仍然存在很多的缺点。
附图说明
被认为是本申请的系统特性的新颖特征在附加的权利要求中被提出。然而，系统自身，还有优选的使用方式，以及进一步的目标和优点，将参照下面与附图相结合进行的详细描述而获得最好的理解，其中参考数字最左边的重要数字表示各个参考数字在其中出现的第一张图，其中：
图1为根据本申请的优选实施例的旋翼飞机的侧视图；
图2为显示图1的旋翼飞机的内部翼肋和尾梁的部分程式化的侧视图；
图3为根据本申请的优选实施例的剪切粘接方法的示意性框图；
图4为根据本申请的优选实施例的尾梁蒙皮的顶视图；
图5为根据本申请的优选实施例的粘接组件的部分程式化顶视图；
图6为根据本申请的优选实施例的图5中的粘接组件的部分程式化侧视图；
图7为用在根据本申请的优选实施例的剪切粘接方法中的使用工具的剖面图；
图8为根据本申请的优选实施例的图7中的工具的部分程式化剖面图；
图9A和9B为根据本申请的优选实施例的粘贴到框架上的粘合组件的程式化侧视图；
图10为根据本申请的优选实施例的粘贴到框架上的粘合组件的透视图；
图11A为根据本申请的优选实施例的粘接固定组件的程式化剖面图；
图11B从图11A中选取的，粘接固定组件的详细视图；
图12为根据本申请的优选实施例的涂敷粘接过程的示意性框图；
图13为从图11A中选取的，粘接固定组件的详细视图；
图14通过图形化方式表示出根据本申请的优选实施例的方法的图表。
图15A和15B为根据本申请的一个替代实施例的粘接固定组件的程式化剖面图；
图16A和16B为根据本申请的一个替代实施例的粘接固定组件的程式化剖面图。
本申请的系统具有各种修改和替代形式，其特定的实施例通过附图中的例子被示出并且在这里详细描述。然而，可以理解的是这里的特定实施例的描述并不是将方法限定于公开的特定形式，而恰好相反，本发明覆盖全部的落入由附上的权利要求所限定的本申请的精神和范围之内的修改，等同方式，以及替代方案。
具体实施方式
本申请的系统的示例性实施例在下面进行描述。为了清楚起见，没有在该说明书中对实际设备的全部特征作说明。当然可以意识到在任意的这样的实施例的发展中，必须做出多种特定实施的决定以实现开发者的特定目标，例如服从系统相关以及商业相关的约束条件，这将使系统从一个方案变化到另一个方案。此外，可以意识到这种发展计划可能是复杂并且耗时的但是仍然是那些得益于本公开的本领域技术人员所从事的常规路径。
在说明书中，参考标记用于表示各种组件之间的空间关系以及作为附图中描述的装置的组件的各种特征的空间方向。然而，在本领域技术人员完整地阅读了本申请之后可以认识到，这里描述的这些装置，元件，设备，等等可以设置成任何期望的方向。因此，诸如“上方”，“下方”，“上部”，“下部”等术语的使用，或是其它用于描述各中组件之间的空间关系或描述这些组件的特征的空间方向的术语应当被理解为分别描述这些组件之间的相对关系或者这些组件的特征的相对空间关系，这里描述的装置可以定位朝向任何期望的方向。
本申请的剪切粘接方法配置成提高结构物在脱离压热器环境中的粘接性。在一个实施例中，剪切粘接方法配置成将多个框架元件粘接到渐缩的尾梁的内部。这些框架设置在卡口型工具上。具有多层粘膜层的粘接组件被粘贴到每个框架的接合表面上。卡口型工具被插入到尾梁中直到粘接组件与尾梁的内壁相接触。导热砖设置到尾梁的外部。导热砖被控制用于首先实现和维持粘接组件的粘性。在该期间卡口工具被驱动以使得框架相对于尾梁平移，由此涂敷粘性粘合剂并且在胶层上建立主动机械压力直到框架设置在最终位置。导热砖被控制用于实现和维持粘合剂处于必须的固化温度。
参照图1，示出飞机101。飞机101包括连接到机身105的尾梁103。飞机101进一步包括旋翼系统107和起落架109。在图示的实施例中，尾梁103具有一个近似于圆锥形的形状，其前端的直径大于尾部的直径。
参照图2，尾梁103包括尾梁蒙皮111和多个尾梁框架113a-113f。在图示的实施例中，尾梁蒙皮111为长度大约为12英尺的锥形区段。尾梁蒙皮前端的内部直径大约为15英寸，同时尾部端部的内部直径大约为7英寸。尾梁蒙皮111优选地为采用内模线技术制造的碳环氧复合材料部件。每个框架113a-113f优选地为编织碳环氧复合材料，配置用于为尾梁蒙皮111提供结构加固。可以完全地意识到上述的尾梁103的配置视情况而定。尾梁蒙皮111和框架113a-113f可以在几何形状和材料上具有多种变化。
参照图3，通过使用剪切粘接方法301，将框架113a-113f粘接到尾梁蒙皮111的内表面上。剪切粘接方法301包括在步骤303中将传热砖（HTT’s）安装到尾梁蒙皮111上。步骤305包括安装热电偶以控制和监视粘接过程中的温度。步骤307包括准备粘接组件。步骤309包括准备框架113a-113f和尾梁蒙皮111的粘接表面。步骤311包括将框架113a-113f安装到工具701上。步骤313包括将粘接组件501安装到框架113a-113f上。步骤315包括将尾梁蒙皮111安装到工具701上。步骤317包括执行涂抹粘接程序。步骤319包括将尾梁103从工具701上拆解开。前面提到的每一个步骤将在这里作进一步的描述。
步骤303包括将一个或多个传热砖317a-317d安装到尾梁蒙皮111上。再次简要地参照图2，传热砖317a-317d被示意性的示出。每个传热砖317a-317d包括配置用于可控制地将热量提供给尾梁蒙皮111的一个区域的柔韧的导热/阻热材料，所述区域邻近于粘接区域。在一个实施例中，每个传热砖317a-317d包括多个安装到散热器上的条带加热器。在这样的一个实施例中，散热器为一个铍铜合金板。如图2所示，极为贴近的框架113a-113f配置有一个传热砖，例如传热砖317a。应当意识到传热砖317a-317d可以是任何能够为框架113a-113f和尾梁蒙皮111之间的胶层提供热量的热源。进而，传热砖317a-317d不仅可以设置在蒙皮111的外部，还可以设置在蒙皮111或框架113a-113f的内部。
参照图4，传热砖317a被示出安装在尾梁蒙皮111上。一个或多个夹具401可以用于将传热砖317a固定在尾梁蒙皮111的周围。隔热衬垫可以用于围绕在每个传热砖317a-317d的周围，以更有效地促进热量从每个传热砖317a-317d向粘接区域传递，部分地通过减少热逃逸的数量来实现。
步骤305包括安装一个或多个热电偶，以控制和监视在粘接过程中的温度。在优选的实施例中，一个或多个控制热电偶（CTC）连接到每个传热砖317a-317d，并且配置成提供传热砖控制器温度信息，以使得传热砖控制器可以精确地控制每个传热砖317a-317d。此外，一个或多个加热器热电偶（HTC）优选地连接到每个传热砖317a-317d，并且配置成控制每个传热砖317a-317d的温度。进而，一个或多个监控热电偶（MTC）设置在位于每个框架113a-113f与尾梁蒙皮111之间的胶层上。与控制热电偶不同，监控热电偶不是用于控制传热砖317a-317d。更确切地，监控热电偶用于监视胶层中的温度。在一个实施例中，可以为监控热电偶选定最大允许温度警报。如果监控热电偶警报被选定，并且超过最大允许温度，那么警报器被触发并且该事件被记录下来。
步骤307包括准备用于框架113a-113f的定制粘接组件。粘接组件的长度和宽度至少部分地取决于相关的框架113a-113f的几何形状。参照图5和6，示出了一个示例性的粘接组件501。为了清楚起见，这里描述的粘接膜组件501是关于框架113f的；然而，这里关于粘接组件501的论述可以相同地应用于配置用于框架113a-113e的粘接组件。在一个优选的实施例中，粘接组件501包括多个粘膜层，例如粘膜层503，505，和507。每个粘膜层503，505，和507被切成具有长度L1，长度L1与框架元件的圆周长相对应，例如框架113f。粘膜层503和507被切成具有宽度W1，宽度W1配置成覆盖框架113f的粘接表面，同时还提供余量使其能够被修整成期望的形状。在示例的实施例中，W1大约为2.6英寸。粘膜层505的宽度等于W1加上W2。进而，W2大约为0.5英寸以使得卷曲件511由粘膜层505形成。正如这里进一步论述的，卷曲件511为粘膜层505的一个卷起部分，其在粘接过程中在框架113f的边缘形成一个圆角。粘膜层503，505，和507布置成当其设置在框架113f上时，它们的端部部分地重叠。粘膜层503和503分别偏移一个距离D1和D2，在优选的实施例中大约偏离一英寸。
在优选的实施例中，粘膜层503，505，和507为商标名为Cytec-Fiberite公司投放市场的FM300-1K粘膜。应该意识到粘接组件501可以包括具有用于安装所必需的粘接强度的任意类型的粘膜。进而，应当意识到粘接组件501可以由单一的粘膜层形成，同样也可以由多个粘膜层形成。进而，在替代的实施例中，粘接组件501可以由膏状粘接剂形成。在这样的实施例中，使用膏状粘接剂就可以不需要再在粘接区域施加和监视热量。
步骤309包括准备尾梁蒙皮111和框架113a-113f的粘接表面。从粘接表面去除沾污物可以提高粘接剂和粘接表面之间的粘合力。表面沾污物可以使用粗棉布和异丙醇去除。进而，粘接表面可以用磨料机械地研磨，例如采用空气推动的喷钢砂处理枪。还可以用砂纸进行手动打磨。进而，粘接表面采用溶剂清洁。可以意识到已知的各种清理粘接表面的方法都可以用在步骤309中。进而，步骤309还包括对粘接表面进行等离子处理以提高粘接力。
步骤311包括将框架113a-113f安装到工具701上。同时参照图7，工具701为具有中心轴703的卡口型的工具。工具701包括多个配置成分别固定框架113a-113f的固定装置705a-705f。可以意识到框架113a-113f可以以多种形式固定到固定装置705a-705f。在一个实施例中，每个框架113a-113f利用紧固件，例如螺丝钉707固定到相应的固定装置705a-705f。再参照图8，框架113a被示出利用可折叠框架夹具713固定到轴703上。在该实施例中，轴703包括外轴709和可移动的内轴711，可移动内轴711相对于外轴709为可移动的。当内轴711沿着方向715被驱动时，可折叠框架夹具713沿着方向715旋转直到牢固地固定框架113a。可以意识到工具701包括与每个框架113a-113f相关联的框架夹具。优选地在工具指向水平方向时框架113a-113f被固定到工具701。
步骤313包括将粘接组件安装到每个框架113a-113f上。为了清楚起见，这里描述的粘膜组件501是关于框架113f的；然而，这里关于粘接组件501和框架113f的论述同样适用于将粘接组件安装到框架113a-113e上。现在参照图9A，9B和10，粘接组件501被示出处于安装到框架113f上的阶段，与方法301的步骤313相对应。如图9A和9B所示，粘接组件501安装到框架113f的接合面。一个或多个监控热电偶509可选地安装在胶层上。每个监控热电偶509可以使用粘接膜方块901进行安装。在示出的实施例中，方块901为大约二分之一平方英寸大的粘膜方块，优选地与用在粘接组件501中的粘膜材料相同。热风枪可以用于预热框架113f的一部分以使得方块901能够施加到框架113f上。每个监控热电偶509接着设置成倚靠着各个方块907以使得监控热电偶509的接合点设置成位于胶层内部大约0.1-0.2英寸。热风枪同样可以用于部分地加热框架113f的胶层表面以提高粘接组件501和框架113f之间的粘着性。接着，粘接组件501围绕设置在框架113f的胶层表面的周围，如图10所示。粘接卷曲件511沿着框架113f的边缘设置，正好位于胶层表面的外部。粘接组件501根据需要沿着非卷曲边缘进行修整。
步骤315包括将尾梁蒙皮111安装到工具701上。参照图11A和11B，尾梁蒙皮111采用尾梁蒙皮固定装置1105a和1105b定位和固定到工具701上。在优选的实施例中，工具701被配置成使得轴703与框架113a-113f一起被固定，同时尾梁蒙皮111配置成相对于轴703平行移动。在替代的实施例中，尾梁蒙皮111被固定，同时轴703被配置成相对于轴703平行移动。在优选的实施例中，在实施步骤317之前工具701被垂直转动。驱动器1101可操作地与工具701相关联以选择性地沿着相对于轴703沿着方向1107平行移动尾梁蒙皮111和蒙皮固定装置1105a和1105b。如在这里关于步骤317的进一步论述，控制系统1103被配置成决定尾梁蒙皮111的平移速度。在优选的实施例中，控制系统1103为具有硬件和软件的计算机，配置成有效并且精确地控制尾梁蒙皮111的平移以及涂敷粘接过程317的其它步骤。
传热砖控制系统1109和驱动器控制系统1103，以及用于运行方法317的其它系统的具体实施方案包括一个或多个计算机，所述计算机包括一个或多个配置用于执行下面描述的任务的处理器和存储器。这可以包括，例如，计算机具有中央处理单元（CPU）和存储用于命令CPU执行至少一些这里描述的任务的软件指令的非易失性存储器。这还可以包括，例如，两个或多个通过计算机网络连接的计算机，其中一个或多个计算机包括CPU和非易失性存储器，并且一个或多个计算机的非易失性存储器存储用于命令任意的CPU执行这里描述的任意任务的软件指令。因此，虽然示例性的实施例是根据离散机进行描述的，可以意识到这种描述是非限制性的，并且当前的描述同样可以应用到多种包括一个或多个执行以任意方式在一个或多个机器之间分配的任务的机器的其它装置中。同样还可以意识到这种机器不需要用于专门执行这里描述的任务，而可以是多用途机器，例如计算机工作站，其同样还适用于执行其它任务。
步骤317包括执行涂敷粘接过程，以在框架113a-113f和尾梁蒙皮111之间建立粘接。步骤317包括获取均匀的粘接剂涂敷以及完全的粘接剂固化。粘接剂涂敷通过尾梁蒙皮111在固定框架113a-113f和粘接组件501上的平移来实现。粘接剂涂敷，与粘接剂固化一样，部分地通过穿过尾梁蒙皮111的导热加热获得提高，热量由传热砖317a-317d提供。传热砖317a-317d由传热砖控制系统1109控制。传热砖317a-317d被控制用于首先加热粘接组件501到期望的粘度，接着在整个涂敷粘接过程中被控制。传热砖317a-317d随后被控制用于固化粘接剂。进而，在粘接剂涂敷和固化过程中，驱动器控制系统1103与传热砖控制系统1109共同起作用。在这些过程中，如这里进一步描述的，采用截然不同的驱动步骤和加热/保温处理阶段。
现在参照图14，图表1401示出胶层温度1403，尾梁平移1405，粘接剂粘度1407，以及固化程度1409之间的关系，其在步骤317中为时间的一个函数。
现在还要参照图12，方法301的步骤317包括第一驱动步骤1201，其中控制系统1103指导驱动器1101平行移动尾梁蒙皮111直到位于每个框架113a-113f上的粘接组件501被带入到与尾梁蒙皮111的内表面相接触。
方法301的步骤317进一步包括第一固化加热阶段1203，其中粘接组件501以一升温速度被传热砖317a-317d加热。在一个优选的实施例中，升温速度大约为每分钟4°华氏温度。
方法301的步骤317进一步包括第二驱动步骤1205，其中每个粘接组件501被压实以压紧粘接组件501，并且排除任何在位于框架113a-113f和尾梁蒙皮111之间的胶层中的残留空气。步骤317中的压实通过相对于框架113a-113f平移尾梁蒙皮111而实现，同时胶层处于预定温度以使得粘接组件501的外部融化成粘性状态。在优选的实施例中，胶层的预定温度大约为130°-160°华氏温度。然而，应当意识到该预定温度视具体情况而定，并且驱动步骤1205可以在粘接组件501的外表面为粘性的任意温度下进行。在优选的实施例中，驱动步骤1205的平移速度大约为0.2英寸每分钟。平移继续进行直到预测的涂敷平移距离被保持。例如，如果预测的涂敷平移距离为0.45英寸，那么步骤1205中的平移在框架113a-113f离框架113a-113f相对于尾梁蒙皮111的最终位置0.45英寸的位置处停止。在优选的实施例中，平移距离大约为0.55英寸；然而，该距离部分地取决于每个粘接501的厚度，还有框架113a-113f和尾梁蒙皮111的几何公差。
方法301的步骤317进一步包括第一固化保温温度阶段1207，其中当平均胶层温度处于预定涂敷温度时升温速度（大约4°华氏温度每分钟）被暂停。在优选的实施例中，预定涂敷温度大约为205°华氏温度。应当可以意识到涂敷温度视情况而定并且部分地取决于使用的特定粘接膜。
方法301的步骤317进一步包括第三驱动步骤1209，其中尾梁蒙皮111被平移直到框架113a-113f到达尾梁蒙皮111上的预定最终位置。在优选的实施例中，涂敷平移速度大约为0.1英寸每分钟并且涂敷平移距离大约为0.45英寸。驱动步骤1209包括将粘接组件501涂敷在胶层上。由于尾梁蒙皮111的锥形形状，平移导致框架113a-113f和尾梁蒙皮111之间的相对厚度减小。平移还导致在粘接组件501为粘性并且被涂敷时在胶层上产生机械性压力。一旦框架113a-113f到达尾梁蒙皮111上的预定最终位置，涂敷平移结束。
方法301的步骤317进一步包括第二固化加热阶段1211，其中胶层以一个加热速度被加热直到得到固化温度。在优选的实施例中，加热阶段1211的升温速度大约为4°华氏温度每分钟。
方法301的步骤317进一步包括第二固化保温温度阶段1213，其中胶层在预定固化温度下被固化预定的固化时间。在优选的实施例中预定固化温度大约为355°华氏温度，同时预定固化时间大约为100分钟。在固化时间完成后，传热砖317a-317d被翻转过来并且该组件被允许冷却到室温。在固化保温温度阶段1213结束时，框架113a-113f被牢固地粘接到尾梁蒙皮111。
再次参照图3，方法301的步骤319包括将尾梁103从工具701上拆卸下来。在步骤319中，尾梁蒙皮111和框架113a-113f从工具701断开。步骤319还包括在胶层中移除任意的监控热电偶509。
参照图13，示出框架113c和尾梁蒙皮111之间固化的胶层1301处于固化状态。由于在涂敷粘接过程317中的压缩和涂敷，固化的胶层1301的厚度比粘接组件501的原始厚度要薄。在涂敷粘接过程317中，卷曲件511变成一个圆角1303。由于卷曲件511在涂敷粘接过程317中设置在前缘，卷曲件511提供允许圆角1303的形成所必须的一定量的粘接剂。优选地，涂敷粘接过程317由于涂敷粘接剂的累积还产生一个后缘圆角1305。进而，涂敷粘接过程317还产生一个残留粘接剂形成的残留尾迹1307。残留尾迹1307的长度取决于在涂敷粘接过程317中累积的涂敷距离。残留尾迹1307可以通过在插入到工具701之前在尾梁蒙皮111上铺设剥离胶带而被移除。
参照图15A和15B，方法301的一个替代的实施例包括使用工具固定装置1501。工具固定装置1501包括使用连接到框架113c的配重物1503。配重物1503可以用于代替相对于尾梁蒙皮111平移框架113c的机械驱动器。挡块1505用于在期望的停止点阻止平移。配重物1503作用于在涂敷平移过程中自行调整的框架113c上。应当意识到尽管仅仅示出单个框架113c，如图11A所示，配重物1503可以连接到多个框架。
参照图16A和16B，方法301的一个替代实施例包括将外部框架1607附着到蒙皮111上。在这样的实施例中，框架1607或者蒙皮111可以借助配重物1603进行平移，配重物1603使用重力向下拉动蒙皮111朝向挡块1605移动。挡块1605用于在期望的停止点阻止平移。在示出的实施例中，传热砖317b可以设置在工具和框架1607之间。应当意识到尽管仅仅示出单个框架113c，如图11A所示，配重物1603可以用于多个框架。进而，应当意识到机械驱动器可以用于代替配重物1603来平移蒙皮111。
这里描述的方法301涉及一种用于飞机的尾梁；然而，应当可以意识到方法301可以用于多种应用。例如，方法301可以用于将框架元件粘接到火箭，飞机，或其它需要内部框架元件的渐缩或锥形的主体的蒙皮上。进而，方法301可以用于非圆锥形的主体上。例如，方法301可以用于将框架元件粘接到机翼形状的主体上，例如机翼元件，旋翼桨叶，尾梁元件，仅举几个例子。同样还应该意识到尽管这里描述的方法301涉及多个框架113a-113f，方法301也可以执行用于将单个框架元件粘接到蒙皮上。
本申请的方法具有显著的先进性，包括：（1）在框架和蒙皮之间产生优质的压热粘接而无需使用压热器；（2）在非压热环境里使用高温固化粘接膜；（3）利用剪切角度和过盈配合在胶层中产生压力；以及（4）在粘接过程中采用较高粘性的薄膜粘接剂产生大的剪切位移。
上面描述的特定的实施例仅限于说明目的，本申请可以以对本领域的技术人员来说是显而易见的不同但是等效的方式进行修改和实施，其都享有这里的教导的利益。进而，这里示出的结构或设计的细节都是非限制性的，不同于下面的权利要求中所描述的。因此，显而易见的是上面公开的特定实施例可以被改变或修改并且所有的这些变化都被认为位于本申请的精神和范围之内。因此，这里请求的保护范围在下面的权利要求中提出。显而易见的是具有显著优点的系统被表述和图示。尽管本申请的系统以限定数量的形式被示出，其并不局限于这些形式，而是可以具有多种可修改的变化和改进而不会脱离其精神的范围。

Claims (25)

1.一种将框架粘接到蒙皮的方法，该方法包括：
将粘接组件设置到框架的接合表面上；
将框架固定到工具上，该工具包括一个轴；
将蒙皮固定到位于工具上的蒙皮固定装置；
执行涂敷粘接过程，该涂敷粘接过程包括：
相对于框架平移蒙皮，直到粘接组件与蒙皮的内表面相接触；
从蒙皮外部加热，以至少部分地改变粘接组件的粘性；
通过相对于框架平移蒙皮来压实粘接组件，以便受压地涂敷粘接组件；以及
当框架处于相对于蒙皮的最终位置时，固化粘接组件。
2.根据权利要求1所述的方法，其中将粘接组件设置到框架的接合表面上的步骤包括：加热框架，以提高粘接组件和框架之间的粘着性。
3.根据权利要求1所述的方法，其中粘接组件包括多个粘膜层。
4.根据权利要求1所述的方法，其中粘接组件包括通过将粘膜层的过剩部分卷起而形成的卷曲件，该卷曲件配置成形成一个位于框架和蒙皮之间的粘接圆角。
5.根据权利要求1所述的方法，其中在通过相对于框架平移蒙皮来压实粘接组件的步骤中存在压缩，所述压缩通过蒙皮的渐缩而产生。
6.根据权利要求1所述的方法，其中蒙皮为渐缩的尾梁。
7.根据权利要求1所述的方法，其中蒙皮和框架中的至少一个为复合材料。
8.根据权利要求1所述的方法，其中将框架固定到工具上的步骤包括：相对于轴平移内轴，以驱动锁闭机构以便将框架固定到工具上。
9.根据权利要求1所述的方法，其中相对于框架平移蒙皮的步骤采用驱动器控制系统来执行，当轴保持不动时，所述驱动器控制系统能够精确地平移蒙皮固定装置和蒙皮。
10.根据权利要求1所述的方法，其中从蒙皮外部加热的步骤包括：选择性地控制传热砖，传热砖设置在蒙皮的外表面上。
11.根据权利要求1所述的方法，其中从蒙皮外部加热的步骤包括：使用计算机自动地控制由设置在蒙皮的外部上的传热砖施加的加热水平。
12.根据权利要求1所述的方法，进一步包括：
使用计算机分析数据，所述数据来自于设置在框架和蒙皮之间的热电偶。
13.根据权利要求1所述的方法，其中固化粘接组件的步骤包括：施加热量，以在固化期间维持固化温度。
14.根据权利要求1所述的方法，其中粘接组件包括粘膜层。
15.根据权利要求1所述的方法，其中粘接组件包括粘接剂糊状层。
16.根据权利要求1所述的方法，其中施加热量的步骤包括：从蒙皮的外部施加热量。
17.根据权利要求1所述的方法，其中通过平移蒙皮压实粘接组件的步骤通过将配重物连接到蒙皮以使其重力作用于平移蒙皮而实现。
18.根据权利要求1所述的方法，其中框架位于蒙皮的外部。
19.一种用于将框架粘接到蒙皮的系统，该系统包括一个或多个处理单元和非易失性存储器，所述非易失性存储器存储计算机可读指令用于：
相对于框架平移蒙皮，直到设置在所述框架和蒙皮之间的粘接组件与蒙皮的内表面相接触；
施加热量，以至少部分地改变粘接组件的粘性；
通过相对于框架平移蒙皮压实粘接组件，以便涂敷粘接组件的同时产生施加到粘接组件上的压缩力；以及
当框架处于相对于蒙皮的最终位置时，固化粘接组件。
20.根据权利要求19所述的系统，进一步包括计算机可读指令，其用于在固化步骤之前施加热量以使粘接组件进入到完全胶粘状态。
21.根据权利要求19所述的系统，其中相对于框架平移蒙皮的步骤通过控制选择性地操作驱动器的驱动器控制系统来实现，驱动器可操作地与蒙皮相关联。
22.一种飞机的尾梁，该尾梁包括：
锥形的尾梁蒙皮；
多个粘接到尾梁蒙皮内部的框架，每个框架具有在每个框架和尾梁蒙皮之间关联的固化胶层；
其中，当粘接组件处于胶粘状态时，通过涂敷粘接组件而形成的固化胶层。
23.根据权利要求22所述的尾梁，进一步包括：
接近每个框架的边缘的圆角，由粘接组件的卷曲件形成的圆角促进了在涂敷粘接组件而粘接组件处于胶粘状态的过程中圆角的形成。
24.根据权利要求22所述的尾梁，进一步包括：
当粘接组件处于胶粘状态时，通过涂敷粘接组件而形成的粘接剂残留尾迹。
25.根据权利要求22所述的尾梁，其中每个框架包括框架凸缘，所述框架凸缘具有形状与圆锥形的尾梁蒙皮的内表面相似的表面。
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EP2581214B1 (en) 2014-06-18
CA2788205C (en) 2014-07-29
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US8784604B2 (en) 2014-07-22
BR102012023612A2 (pt) 2014-12-09

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