公开(公告)号：EP2907743A1

公开(公告)日：2015-08-19

申请号：EP14154971.7

申请日：2014-02-13

申请人： Airbus Operations GmbH

发明人： Eilken, Wolfgang ,  Schulze, Wolfgang ,  Tiryaki, Memis ,  Brunner, Stefan

IPC分类号： B64C1/06

CPC分类号： B64C1/12 ,  B64C1/061 ,  B64G1/22 ,  Y10T29/49947

摘要： The present invention provides a method for coupling a first 110 and a second 120 stiffening element for a skin 102 of an aircraft or spacecraft, wherein the first stiffening element has a cross-sectional profile with first 111 and second 112 web portions extending from a flange portion 113 of a predefined width toward the skin. The method comprises a step of forming a coupling zone 114 of the first stiffening element wherein the second web portion is at least partially removed to expose an inner surface 115 of the first web portion, and a step of fastening a coupling element 104-106, for coupling the stiffening elements, to the coupling zone of the first stiffening element. Under a further aspect, the invention provides a stiffening element for a skin of an aircraft or spacecraft, comprising a cross-sectional profile with first and second web portions extending from a flange portion of a predefined width toward the skin, and a coupling zone wherein the second web portion is at least partially removed to expose an inner surface of the first web portion, as well as a shell component comprising such a stiffening element.

摘要翻译： 本发明提供用于耦合第一110和用于飞行器或航天器的皮肤102的第二120加强元件，worin第一加强元件的方法具有与第一111个第二112腹板部分由法兰延伸的横截面轮廓 向皮肤的预定宽度的113个部分。 该方法包括形成一耦合区中的第一加强元件worin第二幅部分至少部分地移除以暴露至所述第一腹板部分的内表面115的114的步骤，和紧固耦合元件104-106的步骤， 用于耦合的加强元件，所述第一加强元件的联接区。 下一个进一步的方面，本发明提供了一个加强元件用于飞行器或航天器的皮肤，包括具有第一和第二腹板部分从朝向皮肤的预定宽度的凸缘部分延伸的横截面轮廓，以及一个耦合区域worin 第二幅部分至少部分地移除以暴露至所述第一腹板部分的内表面上，以及一外壳部件，其包括寻求加强元件。

公开(公告)号：EP2905221B1

公开(公告)日：2018-07-04

申请号：EP14154486.6

申请日：2014-02-10

申请人： Airbus Operations GmbH

发明人： Brunner, Stefan ,  Schulze, Wolfgang ,  Tiryaki, Memis ,  Eilken, Wolfgang

IPC分类号： B64C1/12 ,  B64C3/26 ,  B64F5/00

CPC分类号： B64C1/12 ,  B23P2700/01 ,  B64C1/068 ,  B64C3/26 ,  B64F5/10 ,  B64G1/22 ,  Y10T29/49622 ,  Y10T29/5397

摘要： The present invention provides a method of manufacturing a shell component for an aircraft or spacecraft. The method comprises a step of positioning a skin panel (102), which includes a skin (104) of the aircraft or spacecraft and first and second stringers (111,112) stiffening the skin, opposite a frame (106) having first and second mouseholes (121,122) for receiving the first and second stringers, a step of elastically bending the skin panelm (102), a step of inserting the first stringer (111) into the first mousehole (121), and a step of releasing the elastic bend to insert the second stringer (112) into the second mousehole (122). Under a further aspect, the invention provides an apparatus (200) for manufacturing a shell component for an aircraft or spacecraft, comprising a positioning unit (203) for positioning a skin panel (102), whic h includes a skin (104) of the aircraft or spacecraft and first and second stringers (111,112) stiffening the skin, opposite a frame (106) having first and second mouseholes (121,122) for receiving the first and second stringers (111,112), a bending unit (204) for elastically bending the skin panel (102), an inserting unit (202) for inserting the first stringer (111) into the first mousehole (121), and a control unit (208), which controls the bending unit (204) to release the elastic bend in order to insert the second stringer (112) into the second mousehole (122).

公开(公告)号：EP2905221A1

公开(公告)日：2015-08-12

申请号：EP14154486.6

申请日：2014-02-10

申请人： Airbus Operations GmbH

发明人： Brunner, Stefan ,  Schulze, Wolfgang ,  Tiryaki, Memis ,  Eilken, Wolfgang

IPC分类号： B64C1/12 ,  B64C3/26 ,  B64F5/00

CPC分类号： B64C1/12 ,  B23P2700/01 ,  B64C1/068 ,  B64C3/26 ,  B64F5/10 ,  B64G1/22 ,  Y10T29/49622 ,  Y10T29/5397

摘要： The present invention provides a method of manufacturing a shell component for an aircraft or spacecraft. The method comprises a step of positioning a skin panel (102), which includes a skin (104) of the aircraft or spacecraft and first and second stringers (111,112) stiffening the skin, opposite a frame (106) having first and second mouseholes (121,122) for receiving the first and second stringers, a step of elastically bending the skin panelm (102), a step of inserting the first stringer (111) into the first mousehole (121), and a step of releasing the elastic bend to insert the second stringer (112) into the second mousehole (122). Under a further aspect, the invention provides an apparatus (200) for manufacturing a shell component for an aircraft or spacecraft, comprising a positioning unit (203) for positioning a skin panel (102), whic h includes a skin (104) of the aircraft or spacecraft and first and second stringers (111,112) stiffening the skin, opposite a frame (106) having first and second mouseholes (121,122) for receiving the first and second stringers (111,112), a bending unit (204) for elastically bending the skin panel (102), an inserting unit (202) for inserting the first stringer (111) into the first mousehole (121), and a control unit (208), which controls the bending unit (204) to release the elastic bend in order to insert the second stringer (112) into the second mousehole (122).

摘要翻译： 本发明提供了制造的壳成分，用于在飞机或航天器的方法。 该方法包括定位蒙皮面板（102），其包括硬化的皮肤的飞机或航天器以及第一和第二纵梁（111112）的皮肤（104），一个框架（106）相对的具有第一的工序和第二鼠洞（ 121122），用于接收所述第一和第二纵梁的，可弹性的步骤弯曲皮肤panelm（102），将所述第一桁（111）到所述第一鼠洞（121）的步骤，和释放所述弹性弯曲，以插入的步骤 第二纵梁（112）到第二鼠洞（122）。 下一个另外的方面，本发明提供一种用于制造外壳部件用于在飞机或航天器，用于定位皮肤面板（102）包括定位部（203）的装置（200），其中H包括的皮肤（104） 飞机或航天器以及第一和第二纵梁（111112）加强皮肤，相对的具有框架（106）的第一和第二鼠标的孔（121,122），用于接收所述第一和第二纵梁（111112），弯曲部（204），用于弹性地弯曲所述 用于插入第一纵梁（111）到所述第一鼠洞（121）插入单元（202）的蒙皮壁板（102），以及控制所述弯曲部（204）的控制单元（208），以释放所述弹性弯曲在 为了插入第二纵梁（112）到第二鼠洞（122）。