CN101687287B - 用于制造航空和航天领域中的复合蒙皮的方法 - Google Patents
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Abstract
本发明提供一种用于航空和航天工业的复合蒙皮(10),并提供一种用于制造此类复合蒙皮(10)的方法,所述方法包括以下方法步骤:从连接板(12)去除多余材料(33)以在所述连接板的一端(20)形成对接搭板(22);然后以物对物焊接将所述连接板(12)的另一端(19)连接到蒙皮板(11);接着将另一蒙皮板(13)固定到所述对接搭板(22)以形成所述复合蒙皮(10)。支持本发明的观点包括用物对物焊接代替铆钉。这提供的优点是,减少了所述复合蒙皮(10)的重量以及用于所述复合蒙皮(10)的制造成本。
Description
技术领域
本发明涉及一种用于制造航空和航天领域中的复合蒙皮的方法,还涉及一种复合蒙皮。
背景技术
虽然本发明可用于航空和航天工业的任何领域,但本发明及其基于的问题将参照商用飞机的两机身段的连接进行最详细的说明。
现代商用飞机的机身通过连接多个机身段而制成,所述多个机身段的每一个被单独制造。为此,如图1中的机身纵剖面图所示,一机身段的一蒙皮1必需与另一机身段的另一蒙皮2相连。这目前由横向对接搭板3实现,所述横向对接搭板在所述机身蒙皮的圆周方向上延伸并通过相向两端5、6上的多排铆钉(例如以附图标记4表示)铆接于所述蒙皮1或所述另一蒙皮2之上。
由于所述铆钉对于飞机的重量具有负面作用且例如钻大量的铆钉孔还涉及高的制造成本,如图1所示的已知复合蒙皮需要大量铆钉的事实已被发现是缺点。
发明内容
因此,本发明的目的是提供一种用于制造复合蒙皮的方法以及一种复合蒙皮,通过所述复合蒙皮,飞机的重量被减小且所述复合蒙皮可容易地制造。
按照本发明,该目的由具有权利要求1特征的方法和/或具有权利要求7特征的复合蒙皮实现。
相应地,本发明提供一种用于制造航空和航天领域中的复合蒙皮的方法,所述方法具有以下步骤:从连接板去除多余材料以在其一端形成对接搭板;以物对物焊接将所述连接板的另一端连接到蒙皮板;以及将另一蒙皮板固定到所述对接搭板以形成所述复合蒙皮。
本发明还为航空和航天领域提供一种复合蒙皮,其包括连接板,所述连接板在其一端具有对接搭板;蒙皮板,所述蒙皮板以物对物焊接与所述连接板的另一端相连;以及另一蒙皮板,所述另一蒙皮板固定于所述对接搭板。
支持本发明的观点包括用物对物焊接代替铆钉将上述横向对接搭板的一端连接于所述蒙皮板。
这样一来,可省去大量铆钉。因此,减小了飞机的重量,且可节省由于铆接所消耗的制造成本。
本发明有利的实施例和改进在附加的权利要求中。
按照本发明所述方法的优选改进,通过摩擦搅拌焊、激光焊或电子束焊以物对物焊接实现所述连接板的另一端与所述蒙皮板的连接。摩擦搅拌焊的突出特点是由此方法产生的所述焊接结构仅被轻微改变,因为在摩擦搅拌焊过程中金属不熔化。由于安全原因,在航空和航天领域中,结构的改变通常不能被接受。在这方面,摩擦搅拌焊尤其适合于本发明。
在按照本发明所述方法的另一优选实施例中,所述物对物焊接形成为对接接缝。此类对接接缝可由已知焊接法,尤其是摩擦搅拌焊容易地制造。所述对接接缝的另一突出特点是,由对接接缝连接的两板蒙皮板可形成平坦表面,这在机身表面领域几乎是必须的要求。
在按照本发明所述方法的另一优选实施例中,所述对接搭板通过铆接而固定于所述另一蒙皮板。当连接第一和第二机身段时,其中所述第一机身段包含所述蒙皮板和与之连接的所述连接板并且所述第二机身段包含所述第二蒙皮板,铆接仍然是优选的固定方法,因为其具有高度的可靠性和易于控制质量的特点。
在按照本发明所述方法的另一优选实施例中,去除多余材料包括在所述连接板的另一端去除另一多余材料以形成具有大体Z形横截面的连接板。通过去除所述另一多余材料,可进一步减小飞机的重量。在本专利申请中,将所述术语“Z形横截面”理解为由两基本平行的直角部形成的横截面,所述直角部的纵向部分重叠搭接。在此情况下,所述对接接缝优选设置在所述连接板远离所述搭接部的一端。
在按照本发明所述方法的另一优选实施例中,去除所述多余材料和/或所述另一多余材料由机械或化学方法执行。化学方法特别以非常高度的精确性为特点。
在按照本发明所述复合蒙皮的一优选实施例中,所述蒙皮板和/或所述另一蒙皮板形成为机身蒙皮段。凭借按照本发明的所述复合蒙皮,在机身段领域可节省大量的铆钉。
在按照本发明所述复合蒙皮的另一优选实施例中,所述连接板、所述蒙皮板和/或所述另一蒙皮板由铝或铝合金构成。在所述航空和航天工业中,由于铝或铝合金的高强度和轻质量,其优选于其他金属。还可想到的是,所述连接板、蒙皮板和/或所述另一蒙皮板由其他金属或金属合金制成。
参照附图,参照实施例在和附图,将在下面更详细地对本发明进行说明。
附图说明
图1是现有技术中已知的复合蒙皮例子的剖面图。
图2是按照本发明一实施例的复合蒙皮的剖面图。
1:蒙皮板
2:蒙皮板
3:横向对接搭板
4:铆钉排
10:复合蒙皮
11:蒙皮板
12:连接板
13:另一蒙皮板
14:焊缝
15:横截面
16:部分
17:部分
18:搭接区域
19:端
20:端
22:对接搭板
23:铆钉排
24:铆钉排
25:铆钉排
26:端部
27:端
32:区域
33:区域
具体实施方式
在附图中,除非另外指出,相同的附图标记表示相同或具有相似功能的构件。
图2是按照本发明一实施例的通过复合蒙皮10的剖面图。
所述复合蒙皮10包括蒙皮板11,例如第一机身段;连接板12,所述连接板以物对物焊接与所述蒙皮板相连;以及另一蒙皮板13,例如第二机身段,所述另一蒙皮板固定于所述连接板12。所述蒙皮板11、所述连接板12和所述另一蒙皮板13优选由铝合金制成。
所述连接板12具有大体Z形的横截面15,所述横截面由两平行的、大体直角的部分16、17组成,所述部分在纵向上于区域18搭接。附图标记19和20指所述连接板12相向的两端。
以附图标记22表示的所述连接板12的所述区域形成所述对接搭板,所述对接搭板通过多排,例如三排延伸至图2页面内的铆钉23、24、25铆接于所述另一蒙皮板13的端部26。
所述蒙皮板11通过剖面中示出的摩擦搅拌焊缝14连接到所述连接板12。所述摩擦搅拌焊缝14形成为对接接缝,所述对接接缝将蒙皮板的一端27连接到端部19,端部27主要为蒙皮板11的边缘,端部19远离所述连接板12的部分16的搭接区域18的。
按照本发明一实施例的所述复合蒙皮10的制造方法将说明于下。
具有大体直角横截面的板(即图中的连接板12,具有虚线表示的额外区域32、33)首先经过化学处理,去除所述区域32、33。所述区域32、33存在于所述连接板12相对的两端19、20。
在本发明的另一实施例中,仅去除所述区域33而不去除区域32是完全可以想到的。
随后,所述蒙皮板11通过摩擦搅拌焊接以其端部27与所述连接板12的端部19相连,产生摩擦搅拌焊缝14。所述摩擦搅拌焊缝14延伸入图2的纸面所在平面内。
在下一步骤中,设置所述另一蒙皮板13以搭接所述对接搭板22,如图2所示。
在下一步骤中,通过铆钉排23、24、25将所述端部26铆接于所述对接搭板。
虽然已主要参照优选实施例对本发明进行了说明,但并不局限于此且可进行广泛的修改。
特别是单独步骤的顺序可以改变。
本发明提供一种用于航空和航天工业的复合蒙皮,并提供一种用于制造此类复合蒙皮的方法,所述方法包括以下方法步骤:从连接板去除多余材料以在所述连接板的一端形成对接搭板;然后以物对物焊接将所述连接板的另一端连接到蒙皮板;接着将另一蒙皮板固定到所述对接搭板以形成所述复合蒙皮。支持本发明的观点包括用物对物焊接代替铆钉。这提供了减少了所述复合蒙皮的重量以及用于所述复合蒙皮的制造成本的优点。
Claims (13)
1.一种用于制造航空和航天领域中的复合蒙皮(10)的方法,其特征在于所述方法包括以下步骤:从连接板(12)去除多余材料(33)以在所述连接板的一端(20)形成对接搭板(22);以物对物焊接将所述连接板(12)的另一端(19)连接到蒙皮板(11);以及将另一蒙皮板(13)固定到所述对接搭板(22)以形成所述复合蒙皮(10)。
2.如权利要求1所述的方法,其特征在于:通过摩擦搅拌焊、激光焊或电子束焊实现所述连接板(12)的另一端(19)与所述蒙皮板(11)的所述物对物焊接。
3.如权利要求1或2所述的方法,其特征在于:所述物对物焊接过程被作为对接接缝(14)的制造过程。
4.如权利要求1所述的方法,其特征在于:通过铆接(23,24,25)将所述对接搭板(22)固定到所述另一蒙皮板(13)。
5.如权利要求1所述的方法,其特征在于:去除所述多余材料(33)包括在所述连接板(12)的另一端(19)去除另一多余材料(32)以形成具有大体Z形横截面(15)的所述对接搭板(22)。
6.如权利要求1所述的方法,其特征在于:由机械或化学方法去除所述多余材料(33)。
7.如权利要求5所述的方法,其特征在于:所述另一多余材料(32)通过机械或化学方法去除。
8.一种用于航空和航天工业的复合蒙皮,所述复合蒙皮包括:连接板(12),所述连接板在其一端(20)具有对接搭板(22);蒙皮板(11),所述蒙皮板以物对物焊接与所述连接板(12)的另一端(19)相连;以及另一蒙皮板(13),所述另一蒙皮板固定于所述对接搭板(22)。
9.如权利要求8所述的复合蒙皮,其特征在于:通过摩擦搅拌焊、激光焊或电子束焊,所述蒙皮板(11)以所述物对物焊接与所述连接板(12)的所述另一端(19)连接。
10.如权利要求8所述的复合蒙皮,其特征在于:通过对接接缝(14),所述蒙皮板(11)连接到所述连接板的所述另一端(19)。
11.如权利要求8所述的复合蒙皮,其特征在于:通过铆钉排(23,24,25)将所述另一蒙皮板(13)固定到所述对接搭板(22)。
12.如权利要求8所述的复合蒙皮,其特征在于:所述连接板(12)具有大体Z形的横截面(15)。
13.如权利要求8所述的复合蒙皮,其特征在于:所述蒙皮板(11)和所述另一蒙皮板(13)形成为机身蒙皮段。
Applications Claiming Priority (5)
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US94118207P | 2007-05-31 | 2007-05-31 | |
DE102007025216.3 | 2007-05-31 | ||
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DE102007025216 | 2007-05-31 | ||
PCT/EP2008/055949 WO2008145527A1 (en) | 2007-05-31 | 2008-05-15 | Method for producing a composite skin in the field of aeronautics and astronautics |
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CN101687287B true CN101687287B (zh) | 2011-08-03 |
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US (1) | US9314875B2 (zh) |
EP (1) | EP2155470B1 (zh) |
JP (1) | JP2010527843A (zh) |
CN (1) | CN101687287B (zh) |
AT (1) | ATE495006T1 (zh) |
BR (1) | BRPI0812038A2 (zh) |
CA (1) | CA2684574A1 (zh) |
DE (1) | DE602008004513D1 (zh) |
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RU2476348C2 (ru) | 2013-02-27 |
DE602008004513D1 (de) | 2011-02-24 |
JP2010527843A (ja) | 2010-08-19 |
ATE495006T1 (de) | 2011-01-15 |
EP2155470B1 (en) | 2011-01-12 |
RU2009138450A (ru) | 2011-04-27 |
EP2155470A1 (en) | 2010-02-24 |
US20100196733A1 (en) | 2010-08-05 |
CN101687287A (zh) | 2010-03-31 |
WO2008145527A1 (en) | 2008-12-04 |
CA2684574A1 (en) | 2008-12-04 |
BRPI0812038A2 (pt) | 2014-11-18 |
US9314875B2 (en) | 2016-04-19 |
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