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21. 发明授权

US07914223B2 Determinant assembly features for vehicle structures 有权
标题翻译：车辆结构的决定因素装配特征
公开(公告)号：US07914223B2
公开(公告)日：2011-03-29
申请号：US12350504
申请日：2009-01-08
申请人： Jeffrey H. Wood , Michael P. Renieri , Thomas R. Berkel
发明人： Jeffrey H. Wood , Michael P. Renieri , Thomas R. Berkel
IPC分类号： F16B9/00
CPC分类号： B64C1/06 , B64C2001/0072 , B64C2001/0081 , F16B2200/10 , Y02T50/43 , Y10T29/49826 , Y10T403/1624 , Y10T403/3906 , Y10T403/4605 , Y10T403/472 , Y10T403/7096 , Y10T403/73 , Y10T403/75
摘要： A determinant assembly feature for a joint assembly and a method of assembly therefor. The joint assembly includes a structure and a web connected thereto. The structure includes a base, a pair of legs extending from the base to define a channel, and one or more location control receiving elements in either leg. The web includes a thickness control element and one or more location control elements correspondingly matched to the location control receiving elements. The method includes providing a structure comprising a base, a pair of legs extending from the base to define a channel and one or more location control receiving elements in either leg; providing a web comprising one or more location control elements and a thickness control element; and inserting the web into the structure, wherein the one or more location control elements is correspondingly matched to the one or more location control receiving elements.
摘要翻译：用于接头组件的决定性组件特征及其组装方法。接头组件包括与其连接的结构和腹板。该结构包括底座，从基座延伸以限定通道的一对腿以及两腿中的一个或多个位置控制接收元件。卷筒纸包括厚度控制元件和对应地与位置控制接收元件匹配的一个或多个位置控制元件。该方法包括提供一种结构，该结构包括基座，从基座延伸以限定通道的一对腿部以及任一腿部中的一个或多个位置控制接收元件; 提供包括一个或多个位置控制元件和厚度控制元件的网; 以及将所述网络插入到所述结构中，其中所述一个或多个位置控制元件对应地与所述一个或多个位置控制接收元件匹配。

22. 发明申请

US20110056066A1 METHOD OF PREPARING THE CONNECTION BETWEEN TWO FUSELAGE SECTIONS OF AN AIRCRAFT 有权
标题翻译：准备飞机两个熔接部分之间的连接的方法
公开(公告)号：US20110056066A1
公开(公告)日：2011-03-10
申请号：US12789308
申请日：2010-05-27
申请人： Pierre ALVEZ
发明人： Pierre ALVEZ
IPC分类号： B23P17/00 , B64C1/00 , B23B49/02
CPC分类号： B21J15/14 , B21J15/142 , B23B35/00 , B23B2215/04 , B23P2700/01 , B64C1/069 , B64C2001/0081 , B64F5/10 , Y10T29/49895 , Y10T29/49956 , Y10T29/4998 , Y10T408/08
摘要： A method is provided for connecting two fuselage sections. A less complicated and time consuming method was found by using High-Speed-Drilling (HSD) for a group of final bore holes through the outer skin of at least one fuselage section and/or the coupling using one drilling template preferably without any pilot drilling.
摘要翻译：提供一种用于连接两个机身部分的方法。通过使用高速钻孔（HSD）通过至少一个机身部分的外皮和/或联接器使用高速钻孔（HSD），优选地不使用任何先导钻孔来实现较不复杂和耗时的方法。

23. 发明授权

US07891606B2 Aircraft comprising a landing gear compartment permitting better integration of the landing gear 有权
标题翻译：包括起落架舱的飞行器允许起落架更好地整合
公开(公告)号：US07891606B2
公开(公告)日：2011-02-22
申请号：US11898550
申请日：2007-09-13
申请人： Bernard Guering
发明人： Bernard Guering
IPC分类号： B64C25/18 , B64C24/34
CPC分类号： B64C1/18 , B64C1/061 , B64C25/04 , B64C25/14 , B64C25/36 , B64C2001/0081 , B64C2025/008 , B64C2025/125
摘要： An aircraft includes a gear compartment in which is adapted to be disposed a raisable forward landing gear, the landing gearing comprising at least one gear leg connected to the aircraft structure and supporting at least one pair of wheels disposed on opposite sides of the gear leg, an articulation part to incline at least one wheel relative to the lifting plane of the landing gear, the gear compartment including an upper panel serving as a floor, with at least one hollow shape F enclosing as closely as possible the at wheels when the landing gear is in raised position.
摘要翻译：飞机包括齿轮室，其中适于设置可抬起的前起落架，起落架包括至少一个连接到飞行器结构的齿轮支撑并且支撑设置在齿轮支腿的相对侧上的至少一对轮子，一个关节部分，其相对于起落架的提升平面倾斜至少一个车轮，该齿轮室包括一个用作地板的上部面板，其中至少一个中空形状F尽可能地紧密地包围在起落架处于上升位置。

24. 发明申请

US20100223772A1 Structural Panels for Use in Aircraft Fuselages and Other Structures 有权
标题翻译：用于飞机机身和其他结构的结构面板
公开(公告)号：US20100223772A1
公开(公告)日：2010-09-09
申请号：US12762129
申请日：2010-04-16
申请人： Kent Johnson , Mark A. Ulvin
发明人： Kent Johnson , Mark A. Ulvin
IPC分类号： B25B27/14 , B32B3/06
CPC分类号： B61D17/041 , B63B3/28 , B63B3/36 , B64C1/12 , B64C3/182 , B64C3/26 , B64C2001/0072 , B64C2001/0081 , Y02T50/43 , Y10T29/49616 , Y10T29/49622 , Y10T29/53978 , Y10T156/1089 , Y10T428/24033 , Y10T428/24174 , Y10T428/24182 , Y10T428/24198
摘要： Structural panels for use in manufacturing aircraft fuselages and other structures are disclosed herein. In one embodiment, a structural panel configured in accordance with the invention includes a skin and at least first and second stiffeners. The first stiffener can have a first flange portion mated to the skin and a first raised portion projecting away from the skin. The second stiffener can have a second flange portion mated to the skin and a second raised portion projecting away from the skin. At least one of the first flange portion of the first stiffener and the second flange portion of the second stiffener can extend toward the other of the first flange portion and the second flange portion to form an at least approximately continuous support surface to which a frame can be attached.
摘要翻译：本文公开了用于制造飞机机身和其它结构的结构面板。在一个实施例中，根据本发明构造的结构面板包括皮肤和至少第一和第二加强筋。第一加强件可以具有与皮肤配合的第一凸缘部分和远离皮肤突出的第一凸起部分。第二加强件可以具有与皮肤配合的第二凸缘部分和远离皮肤突出的第二凸起部分。第一加强件的第一凸缘部分和第二加强件的第二凸缘部分中的至少一个可以朝向第一凸缘部分和第二凸缘部分中的另一个延伸，以形成至少近似连续的支撑表面，框架可向该支撑表面被附上

25. 发明授权

US07686249B2 Integral frame member for an aircraft 有权
标题翻译：飞机的整体架构件
公开(公告)号：US07686249B2
公开(公告)日：2010-03-30
申请号：US10551019
申请日：2004-03-29
申请人： Helmut Lüttig , Carsten Paul
发明人： Helmut Lüttig , Carsten Paul
IPC分类号： B64C1/06
CPC分类号： B64C1/061 , B64C2001/0081 , Y02T50/42
摘要： According to an exemplary embodiment of the present invention, a frame member for an aircraft is provided comprising a clip region and a frame region. According to an aspect of this exemplary embodiment of the present invention, the clip region, shear web region and the frame region are integrated into the frame member and be formed from an extrusion mold by a milling process. Advantageously, this allows for a reduced number of individual elements for forming a frame member and provides the flexibility of variation of the forms and dimensions of a frame member for an aircraft.
摘要翻译：根据本发明的示例性实施例，提供了一种用于飞机的框架构件，其包括夹子区域和框架区域。根据本发明的该示例性实施例的一个方面，夹持区域，剪切腹板区域和框架区域被整合到框架构件中并且通过铣削加工由挤压模具形成。有利地，这允许减少数量的单个元件以形成框架构件并且提供用于飞行器的框架构件的形式和尺寸的变化的灵活性。

26. 发明申请

US20100038489A1 LIGHTWEIGHT STRUCTURE 有权
标题翻译：轻型结构
公开(公告)号：US20100038489A1
公开(公告)日：2010-02-18
申请号：US12509008
申请日：2009-07-24
申请人： Rolf Bense , Steffen Biesek , Robert Alexander Goehlich , Karl-Hinrich Herbst , Michael Kreimeyer , Chiristian Kulik , Marco Pacchione
发明人： Rolf Bense , Steffen Biesek , Robert Alexander Goehlich , Karl-Hinrich Herbst , Michael Kreimeyer , Chiristian Kulik , Marco Pacchione
IPC分类号： B64C1/06
CPC分类号： B64C1/12 , B64C1/069 , B64C2001/0081 , Y02T50/42
摘要： A lightweight structure is disclosed, in particular a lightweight structure for an aircraft which is formed from a large number of components which can be joined together by weld joining processes. According to the invention, the lightweight structure has a component thickness which is increased corresponding to the loads in the joint region of the at least one welded joint compared to a thickness of the component outside the joint region.
摘要翻译：公开了一种轻质结构，特别是用于飞机的轻型结构，其由大量可通过焊接连接工艺连接在一起的部件形成。根据本发明，轻质结构具有相对于至少一个焊接接头的接合区域中的负载而增加的部件厚度，与组件外部的接合区域的厚度相比较。

27. 发明申请

US20100025531A1 Aircraft-fuselage assembly concept 失效
标题翻译：飞机机身装配概念
公开(公告)号：US20100025531A1
公开(公告)日：2010-02-04
申请号：US12308931
申请日：2006-06-28
申请人： Günter Pahl
发明人： Günter Pahl
IPC分类号： B64C1/00 , B21D53/88
CPC分类号： B64C1/068 , B64C1/061 , B64C2001/0072 , B64C2001/0081 , Y02T50/43 , Y10T29/49622
摘要： An aircraft fuselage section includes a first interior tube as well as a second interior tube that are produced in an upstream production step, which interior tubes are subsequently enclosed by an exterior tube. For spacing and in order to provide more stability to the tubes the interior tubes are enclosed by straps that are arranged between the interior tubes and the exterior tube.
摘要翻译：飞机机身部分包括在上游制造步骤中制造的第一内部管和第二内部管，该内部管随后被外部管封闭。为了间隔并且为了向管提供更多的稳定性，内部管被布置在内部管和外部管之间的带包围。

28. 发明申请

US20090266936A1 AIRCRAFT FUSELAGE STRUCTURAL COMPONENTS AND METHODS OF MAKING SAME 审中-公开
标题翻译：飞机熔接结构件及其制造方法
公开(公告)号：US20090266936A1
公开(公告)日：2009-10-29
申请号：US12111825
申请日：2008-04-29
申请人： Fernando Ferreira Fernandez , Sadao Takanashi , Lucio Camargo Fortes , Marcio Cruz , Marcelo Galvao do Prado , Clovis Augusto Eca Ferreira , Jose Donizette Aguiar
发明人： Fernando Ferreira Fernandez , Sadao Takanashi , Lucio Camargo Fortes , Marcio Cruz , Marcelo Galvao do Prado , Clovis Augusto Eca Ferreira , Jose Donizette Aguiar
IPC分类号： B64C1/00 , B64F5/00
CPC分类号： B64C1/061 , B64C1/064 , B64C2001/0081
摘要： Aircraft fuselage structures have reinforcement members in the vicinity of the stringer openings formed in frame members and are rigidly lap joined to a surface region of the frame members by a friction stir weld region. Such aircraft fuselage structural components may thus be provided with plural longitudinally spaced-apart frame members defining a transversal cross-section of an aircraft fuselage section, the frame members having a plurality of stringer holes therethrough, and plural longitudinally oriented stringers each being positioned within a respective one of the stringer holes of the frame member. The reinforcement members are lap joined to corresponding surfaces of frame members in the vicinity of the stringer holes such that the reinforcement members are joined rigidly to the corresponding surfaces of the frame members by a friction stir weld region.
摘要翻译：飞行器机身结构在框架构件中形成的纵梁开口附近具有加强构件，并通过摩擦搅拌焊接区域刚性地搭接到框架构件的表面区域。这样的飞机机身结构部件因此可以设置有限定飞机机身部分的横截面的多个纵向间隔开的框架构件，框架构件具有穿过其中的多个纵梁孔，并且多个纵向定向的纵梁各自位于相应的一个框架构件的纵梁孔。加强构件在纵梁孔附近搭接到框架构件的对应表面，使得加强构件通过摩擦搅拌焊接区域刚性地连接到框架构件的对应表面。

29. 发明申请

US20090101756A1 MONOLITHIC SELF-STIFFENED PANELS 有权
标题翻译：单一自强度面板
公开(公告)号：US20090101756A1
公开(公告)日：2009-04-23
申请号：US11996302
申请日：2006-07-12
申请人： Bruno Cacciaguerra
发明人： Bruno Cacciaguerra
IPC分类号： B64C1/12
CPC分类号： B64C25/16 , B64C1/12 , B64C2001/0072 , B64C2001/0081 , Y02T50/43
摘要： A composite panel having a first skin forming the outer wall of the panel, known as the lower face (1), and a second skin forming part of the inner wall of the panel. The second skin is formed hollow such as to produce an inner reinforcing frame (2) in the form of a half-box structure (3) which, together with the first skin, forms box parts. The aforementioned frame is equipped with a rim (4a, 4b) for fixing to the first skin, a face known as the upper face (5) and connecting side walls (6, 6a, 6b, 6c, 6d, 6e, 7) between the rim (4a, 4b) and the upper face (5) the first and second skins forming a monolithic self-stiffened panel. The half-box frame (2) has perforated sections (8) which are defined by hollow beam sections forming the half-box frame (2).
摘要翻译：一种复合面板，其具有形成面板外壁的第一皮肤，称为下表面（1），以及形成面板内壁部分的第二皮肤。第二皮肤形成为中空的，以产生半框结构（3）形式的内部加强框架（2），其与第一皮肤一起形成箱体部件。上述框架配备有用于固定到第一皮肤的边缘（4a，4b），称为上表面（5）的表面和连接侧壁（6,6a，6b，6c，6d，6e，7）之间的边缘边缘（4a，4b）和上表面（5），第一和第二表皮形成一体的自加强板。半框框架（2）具有由形成半框框架（2）的中空梁部分限定的穿孔部分（8）。

30. 发明授权

US07494092B2 Lightweight structural component in particular for aircraft and method for its production 有权
标题翻译：轻型结构部件，尤其适用于飞机及其生产方法
公开(公告)号：US07494092B2
公开(公告)日：2009-02-24
申请号：US10757419
申请日：2004-01-15
申请人： Berndt Brenner , Bernd Winderlich , Jens Standfuβ , Jörg Schumacher , Hartmut Brenneis , Walter Zink
发明人： Berndt Brenner , Bernd Winderlich , Jens Standfuβ , Jörg Schumacher , Hartmut Brenneis , Walter Zink
IPC分类号： B64C1/06
CPC分类号： B64C1/12 , B64C2001/0081 , Y02T50/42 , Y10T29/49867
摘要： Lightweight structural component including at least one panel and at least one stiffening element oriented one of lengthwise and crosswise. The at least one stiffening element includes two side pieces. Each of the two side pieces is at least partially connected to the panel in a material-locking manner. The two side pieces are connected to the panel at two separate joint zones. A method of producing the lightweight structural component includes milling the at least one panel to form at least one thickened region and joining the two side pieces to the at least one panel at the two separate joint zones. This Abstract is not intended to define the invention disclosed in the specification, nor intended to limit the scope of the invention in any way.
摘要翻译：轻质结构部件包括至少一个板和至少一个纵向和横向的加强元件。所述至少一个加强元件包括两个侧片。两个侧片中的每一个以材料锁定的方式至少部分地连接到面板。两个侧片在两个单独的接合区域连接到面板。制造轻质结构部件的方法包括铣削至少一个面板以形成至少一个加厚区域，并且将两个侧部件连接到两个分开的接合区域处的至少一个面板。本摘要不旨在限定说明书中公开的发明，也不旨在以任何方式限制本发明的范围。

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