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51. 发明申请

WO2008113612A4 GAP COVERING DEVICE 审中-公开
标题翻译： GAP覆盖设备
公开(公告)号：WO2008113612A4
公开(公告)日：2009-03-05
申请号：PCT/EP2008002353
申请日：2008-03-25
申请人： AIRBUS GMBH , AIRBUS SAS , BOCK THOMAS , AUBURGER MICHAEL , DOEMELAND PATRIQUE , GERNER BRIGITTE , SCHUEPHAUS FLORIAN , FIEDLER SILVAN
发明人： BOCK THOMAS , AUBURGER MICHAEL , DOEMELAND PATRIQUE , GERNER BRIGITTE , SCHUEPHAUS FLORIAN , FIEDLER SILVAN
IPC分类号： B64C1/00 , B64C1/06 , B64C1/12
CPC分类号： B64C1/066
摘要： A gap covering device (10) for covering a gap (16) between two mutually adjacent first aircraft interior components (12, 14) comprises a visible portion (18) as well as a retaining portion (20) connected to the visible portion (18) and extending opposite the visible portion (18). A receiving structure is fastened to an inner surface of the visible portion (18) and/or of the retaining portion (20) and has a receiving contour adapted to an edge contour of the first aircraft interior components (12, 14).
摘要翻译：用于覆盖两个彼此相邻的第一飞行器内部部件（12,14）之间的间隙（16）的间隙覆盖装置（10）包括可见部分（18）以及连接到可见部分（18）的保持部分（20））并且与可见部分（18）相对延伸。接收结构紧固到可见部分（18）和/或保持部分（20）的内表面，并具有适于第一飞行器内部部件（12,14）的边缘轮廓的接收轮廓。

52. 发明申请

WO2008151843A4 ENGINE NACELLE OF AN AIRCRAFT COMPRISING A VORTEX GENERATOR ARRANGEMENT 审中-公开
标题翻译：包含VORTEX发电机装置的飞机的发动机
公开(公告)号：WO2008151843A4
公开(公告)日：2009-02-26
申请号：PCT/EP2008004841
申请日：2008-06-16
申请人： AIRBUS GMBH , SCHWETZLER DETLEV
发明人： SCHWETZLER DETLEV
IPC分类号： B64C7/02 , B64C23/06 , B64D29/02
CPC分类号： B64C7/02 , B64C23/06 , B64D29/02 , Y02T50/162
摘要： An engine nacelle of an aircraft, which engine nacelle on one side comprises several fin-shaped vortex generators (3, 4, 5) so that with an increase in the angle of attack, to improve maximum lift, the field of vorticity generated by said vortex generators (3, 4, 5) overall extends over an increasing region of the wing in the direction of the wingspan, with the first vortex generator being located within a positioning corridor (K31) situated between two boundary lines (51, 52), wherein: the starting point (51 a) of the first boundary line (51) is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi = 35 degrees and the engine-nacelle longitudinal coordinate X = L/4; the end point (51 b) of the first boundary line (51 ) is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi = 25 degrees and the engine-nacelle longitudinal coordinate X = L·2/3; the starting point (52a) of the second boundary line (52) is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi = 90 degrees and the engine-nacelle longitudinal coordinate X = L/4; the end point (52b) of the second boundary line (52) is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi = 55 degrees and the engine-nacelle longitudinal coordinate X = L·2/3.
摘要翻译：飞机的发动机机舱，其一侧的发动机舱包括若干鳍形涡流发生器（3,4,5），以便随着迎角的增加，为了改善最大升力，所述涡流产生的涡度场涡流发生器（3,4,5）在翼展方向上总体上延伸到机翼的增加区域上，第一涡流发生器位于位于两个边界线（51,52）之间的定位走廊（K31）内，其中：第一边界线（51）的起点（51a）是发动机舱周向角度phi = 35度，发动机舱纵向坐标X = L / 4的发动机舱的圆周点; 第一边界线（51）的端点（51b）是发动机舱周向角度phi = 25度，发动机舱纵向坐标X = L·2/3的发动机舱的圆周点; 第二边界线（52）的起点（52a）是发动机舱周向角度phi = 90度，发动机舱纵向坐标X = L / 4的发动机舱的圆周点; 第二边界线（52）的端点（52b）是发动机舱的圆周角度phi = 55度，发动机舱纵向坐标X = L·2/3的发动机舱的圆周点。

53. 发明申请

WO2008113613A4 INTERIOR TRIM COMPONENT FOR AN AIRCRAFT CABIN 审中-公开
标题翻译：用于飞机客舱的室内装饰部件
公开(公告)号：WO2008113613A4
公开(公告)日：2009-02-26
申请号：PCT/EP2008002355
申请日：2008-03-25
申请人： AIRBUS GMBH , FEILER MARKUS , VEIHELMANN BERND , VOELKLE DIETMAR
发明人： FEILER MARKUS , VEIHELMANN BERND , VOELKLE DIETMAR
IPC分类号： B64C1/06 , B64C1/12
CPC分类号： B64C1/066 , Y10T29/49826 , Y10T156/10
摘要： An interior trim component (10) for an aircraft cabin comprises a supporting structure which is formed by a first chamber system (12) which is sealable against the outside atmosphere. The first chamber system (12) forming the supporting structure is adapted to be loaded with an internal pressure which is necessary for producing the desired structural load-bearing capacity of said supporting structure.
摘要翻译：一种用于飞机机舱的内饰部件（10）包括支撑结构，该支撑结构由可密封外部大气的第一腔室系统（12）形成。形成支撑结构的第一腔室系统（12）适于被加载内部压力，该内部压力对于产生所述支撑结构的期望的结构承载能力是必需的。

54. 发明申请

WO2009000726A4 DEVICE AND METHOD FOR DETECTING A COMMUNICATION CHANNEL 审中-公开
标题翻译：用于检测通信信道的设备和方法
公开(公告)号：WO2009000726A4
公开(公告)日：2009-02-19
申请号：PCT/EP2008057706
申请日：2008-06-18
申请人： AIRBUS GMBH , KNEFELKAMP SVEN , DURAZ ERIC
发明人： KNEFELKAMP SVEN , DURAZ ERIC
IPC分类号： H04B7/185
CPC分类号： H04B7/18508
摘要： The present invention provides a method and a device for detecting a communication channel in whose frequency band (?f ) radio signals are transmitted by different radio signal sources inside a cabin. In this case a wide band antenna (2) receives the radio signals transmitted inside the cabin. Different demodulators (8) are provided, each of which demodulate the radio signals received by the wide band antenna (2) within an associated frequency range (?F) of the demodulator (8). A configuration logic (4) establishes whether, in a frequency band (?f) within a demodulated frequency range (?F), radio signals are being transmitted simultaneously by different radio signal sources, in the case of impermissible signal transmissions of a radio signal source, e.g. when a non-safety-relevant system transmits signals in the same frequency band (?f ) of a safety- relevant system in the same frequency bands ?f of a safety-relevant system, the non-safety-relevant system is reconfigured by the configuration logic and an alarm or warning signal is generated as an indication of the impermissible condition.
摘要翻译：本发明提供了一种用于检测通信信道的方法和装置，其中其频带（Δf）无线电信号由机舱内的不同无线电信号源发送。在这种情况下，宽带天线（2）接收在机舱内传输的无线电信号。提供了不同的解调器（8），每个解调器（8）在解调器（8）的相关联的频率范围（ΔF）内解调由宽带天线（2）接收的无线电信号。配置逻辑（4）确定在解调频率范围（ΔF）内的频带（Δf）中无线电信号是否被不同的无线电信号源同时传输，在无线电信号的不允许的信号传输的情况下来源，例如当非安全相关系统在与安全相关系统的相同频带αf中的安全相关系统的相同频带（Δf）中传输信号时，非安全相关系统由产生配置逻辑和报警或警告信号作为不允许条件的指示。

55. 发明申请

WO2008142091A3 PICO CELL AND CONTROL METHOD FOR THE WIRELESS DATA TRANSMISSION IN AN AIRPLANE AND AIRPLANE 审中-公开
标题翻译：微微蜂窝和控制方法研究无线数据传输在飞机和飞机
公开(公告)号：WO2008142091A3
公开(公告)日：2009-01-15
申请号：PCT/EP2008056227
申请日：2008-05-21
申请人： AIRBUS GMBH , MUELLER JAN , TRUSCH HEIKO
发明人： MUELLER JAN , TRUSCH HEIKO
IPC分类号： H04B7/185
CPC分类号： H04B7/18506
摘要： The invention relates to a pico cell in an airplane (1) for the wireless data transmission between at least one mobile station (3) in the airplane and a base station (2) in the airplane, wherein a communication link can be established in a terrestrial communication network (6) between the at least one mobile station (3) and a subscriber (7, 8, 9) via the base station (2). The invention also relates to a method for operating such a pico cell. In order to automatically inform the airplane passengers on the authorization or interdiction of use of their mobile phone devices, at least one display device is provided in the airplane for displaying the availability of the pico cell in the airplane.
摘要翻译：本发明涉及一种微小区在用于数据的至少一个移动站之间的无线传输的飞行器（1）（3）在平面中和在飞行器中的基站（2），其中，经由所述基站（2）的所述至少一个之间的通信链路一个移动台（3）和一个用户（7，8，9）的一个地面通信网络（6）可以被建立，以及用于操作这种微微小区的方法。到乘客能够自动指示他们的移动设备的可用性，或在平面上的禁令，在飞机的至少一个显示装置提供了一种用于在飞行器中的微微小区的可用性的指示。

56. 发明申请

WO2008129074B1 AIRCRAFT 审中-公开
标题翻译：飞机
公开(公告)号：WO2008129074B1
公开(公告)日：2008-12-24
申请号：PCT/EP2008054985
申请日：2008-04-24
申请人： AIRBUS GMBH , CERNE GERD
发明人： CERNE GERD
IPC分类号： B64C9/16 , B64C9/22
CPC分类号： B64C9/16 , B64C9/22 , Y02T50/32
摘要： The invention provides an aircraft, comprising a fuselage (8), an airfoil (1) mounted to the fuselage (8) and a flap (2; 3) for steering the aircraft. Furthermore, connecting means (18; 79) articularly connect the flap (2; 3) to the airfoil (1) such that the flap (2; 3) is allowed to rotate around a rotation axis (28; 82) substantial parallel to the trailing or leading edge (4; 5) of the airfoil (1) between a retracted position (I) and an extended position (II) and to translate in a direction (54a; 98) substantially parallel to the rotation axis (28; 82). A rod (43; 95) articularly connect the flap (2; 3) to the airfoil (1) or to the fuselage (8), wherein the rod (43; 95) defines the translation of the flap (2; 3) in the direction (55a; 98) parallel to the rotation axis (28; 82). Hence, by way of the invention, forces acting of the flap (2; 3) in a direction (55a; 98) parallel to the rotation axis (28; 82) can be taken up by the rod (43; 95). Consequently, there is no need for using locating bearings having negative aerodynamic effects due to their by comparison large dimensions in a direction substantially perpendicular to the direction of flight (12) of the aircraft.
摘要翻译：本发明提供了一种飞机，包括机身（8），安装到机身（8）的翼型件（1）和用于转向飞机的翼片（2; 3）。此外，连接装置（18; 79）将翼片（2; 3）专门连接到翼型件（1），使得翼片（2; 3）被允许围绕基本平行于所述翼型件（1）的后缘或前缘（4; 5）在缩回位置（I）和延伸位置（II）之间并且沿基本平行于所述旋转轴线（28; 82）的方向（54a; 98）平移）。杆（43; 95）将翼片（2; 3）专门连接到翼型件（1）或机身（8），其中杆（43; 95）限定翼片（2; 3）的平移平行于旋转轴线（28; 82）的方向（55a; 98）。因此，通过本发明，平行于旋转轴线（28; 82）的方向（55a; 98）作用的翼片（2; 3）的力可被杆（43; 95）吸收。因此，不需要使用具有负气动效应的定位轴承，因为它们通过比较基本上垂直于飞行器的飞行方向（12）的方向的大尺寸。

57. 发明申请

WO2008104529A3 MODULE FOR ACCOMMODATION OF CREW MEMBERS HAVING A STOWAGE BIN USABLE FROM INSIDE THE MODULE 审中-公开
标题翻译：用于存储可用于模块内的堆栈的CREW成员的模块
公开(公告)号：WO2008104529A3
公开(公告)日：2008-11-06
申请号：PCT/EP2008052287
申请日：2008-02-26
申请人： AIRBUS GMBH , WARNER HOLGER , HELFRICH FELIX
发明人： WARNER HOLGER , HELFRICH FELIX
IPC分类号： B64D11/00
CPC分类号： B64D11/003 , B64D11/00 , B64D2011/0076
摘要： According to an exemplary embodiment of the present invention, a module (200) for an aircraft for the accommodation of crew members is stated, which module comprises a trough-shaped floor (215) region having an external contour (211) that corresponds to the contour of further stowage bins (201, 202) installed in the aircraft. The storage space created in this way in the interior of the module (200) is accessible from the interior of the module. In this way the stability of the module (200) may be enhanced and the installation expenditure may be reduced. Furthermore, comfort may be enhanced, in particular as a result of more space being available for the crew.
摘要翻译：根据本发明的示例性实施例，描述了用于机组人员的飞行器的模块（200），该模块包括具有对应于外部轮廓（211）的外部轮廓（211）的槽形地板（215）区域安装在飞机上的进一步装载箱（201,202）的轮廓。以这种方式在模块（200）的内部创建的存储空间可从模块的内部访问。以这种方式，可以增强模块（200）的稳定性，并且可以减少安装支出。此外，舒适性可能会增强，特别是由于机组人员可以使用更多的空间。

58. 发明申请

WO2008090144B1 CONNECTING ELEMENT AND USE OF SUCH A CONNECTING ELEMENT FOR FASTENING AIRCRAFT COMPONENTS IN THE CASE OF A CFK-METAL HYBRID CONSTRUCTION 审中-公开
标题翻译：连接元件和使用这样一个连接元件来加速飞机组件在CFK金属混合结构
公开(公告)号：WO2008090144B1
公开(公告)日：2008-10-09
申请号：PCT/EP2008050692
申请日：2008-01-22
申请人： AIRBUS GMBH , KOLAX MICHAEL , DOLZINSKI WOLF-DIETRICH
发明人： KOLAX MICHAEL , DOLZINSKI WOLF-DIETRICH
IPC分类号： B64D45/02 , B64C1/00 , B64C1/12 , F16B33/00
CPC分类号： B64C1/064 , B64C1/12 , F16B19/06 , Y10T403/18 , Y10T403/75
摘要： The present invention relates to the use of connecting elements (1) for fastening CFK components (2) and metal components (3) in an aircraft or spacecraft, wherein a CFK component (2) and a metal component (3) can be connected to each other via at least one connecting element (1). The connecting element (1) in this case is produced from an electrically non-conducting material, or has a shank (9) and is produced from an electrically conducting or non-conducting material, wherein the shank (9) is provided with a sleeve (10) consisting of an electrically non-conducting material.
摘要翻译：本发明涉及用于将CFK部件（2）和金属部件（3）紧固在飞机或航天器中的连接元件（1）的使用，其中CFK部件（2）和金属部件（3）可以连接到通过至少一个连接元件（1）彼此相连。在这种情况下，连接元件（1）由非导电材料制成，或具有柄（9）并且由导电或非导电材料制成，其中柄（9）设置有套筒（10）由不导电材料组成。

59. 发明申请

WO2008090039B1 DEVICE, IN PARTICULAR CONNECTION ROD, FOR BRACING A FUSELAGE STRUCTURE OF AN AIRCRAFT AND/OR FOR FASTENING A COMPONENT 审中-公开
标题翻译：装置，特别是连接杆，用于制造飞机的熔融结构和/或用于紧固部件
公开(公告)号：WO2008090039B1
公开(公告)日：2008-10-02
申请号：PCT/EP2008050292
申请日：2008-01-11
申请人： AIRBUS GMBH , BENTHIEN HERMANN
发明人： BENTHIEN HERMANN
IPC分类号： B64C1/00 , F16B37/04
CPC分类号： B60P7/0807 , B64D9/00 , B64D9/003 , Y02T50/46
摘要： The invention relates to a device (18, 61), in particular a connection rod (1, 19), for bracing a fuselage structure (9, 10, 27, 28, 45, 74) and/ or for fastening components on the fuselage structure (9, 10, 27, 28, 45, 74). In one embodiment, the joints (29, 30, 53) are integrated into fuselage structure (9, 10, 27, 28, 45) for linking on both sides of connection rod (1, 19) to fuselage structure (9, 10, 27, 28, 45). As a result of the integration of joints (29, 30, 53), a reduced number of individual parts is produced in comparison to previously known embodiments, which leads to a reduction in weight, a reduced maintenance and servicing outlay and an improved reliability against failure. Moreover, device (18, 61) according to the invention enables the introduction of forces in the region of neutral fibres (43, 44) of fuselage structure (9, 10, 27, 28, 45, 74). A further configuration of device (61) provides only a one-sided articulated linking of a component (65) to fuselage structure (74) by means of (first) end portion (63). Second end portion (64) is screwed to fuselage structure (74). To this end, both end portions are provided with a thread at least in sections.
摘要翻译：本发明涉及一种用于支撑机身结构（9,10,27,28,45,74）和/或用于紧固机身上的部件的连接杆（1,19）的装置（18,61），特别是连接杆（1,19）结构（9,10,27,28,45,74）。在一个实施例中，接头（29,30,53）被集成到机身结构（9,10,27,28,45）中，用于在连接杆（1,19）的两侧连接到机身结构（9,10， 27，28，45）。由于接头（29,30,53）的整合，与先前已知的实施例相比，产生了减少数量的单个部件，这导致重量的减轻，减少的维护和维修支出以及改进的可靠性失败。此外，根据本发明的装置（18,61）能够在机身结构（9,10,27,28,45,74）的中性纤维（43,44）的区域中引入力。设备（61）的进一步配置仅通过（第一）端部部分（63）提供部件（65）与机身结构（74）的单侧铰接连接。第二端部（64）旋入机身结构（74）。为此，两个端部至少部分地设置有螺纹。

60. 发明申请

WO2007071384A8 FLEXIBLE CONTROL SURFACE FOR AN AIRCRAFT 审中-公开
标题翻译：飞机的柔性控制面
公开(公告)号：WO2007071384A8
公开(公告)日：2008-09-25
申请号：PCT/EP2006012288
申请日：2006-12-20
申请人： AIRBUS GMBH , GROHMANN BORIS , KONSTANZER PETER , LORKOWSKI THOMAS
发明人： GROHMANN BORIS , KONSTANZER PETER , LORKOWSKI THOMAS
IPC分类号： B64C3/48 , B64C3/50 , B64C9/00
CPC分类号： B64C3/48 , B64C3/50 , B64C9/00
摘要： A flexible control surface (1; 11, 14) comprises at least two actuators (3), which act on the control surface (1; 11, 14) at different points of action (2) which are offset laterally with respect to the circulating-flow direction (6) with respect to one another. The at least two actuators (3) are designed such that the points of action (2) can be deflected differently when the actuators (3) are operated at the same time. It is thus possible to elastically deform the control surface (1; 11, 14), in particular along the span width direction (9), without kinks, in which case it is possible to achieve uniform transitions along the control surface laterally with respect to the flow direction (6). The invention makes it possible to reduce vortices and noise induced by the control surface.
摘要翻译：柔性控制表面（1; 11,14）包括至少两个致动器（3），其在不同的作用点（2）处作用在控制表面（1; 11,14）上，所述不同的作用点（2）相对于循环 - 流方向（6）。至少两个致动器（3）被设计成使得当致动器（3）同时操作时，作用点（2）可以被不同地偏转。因此，可以使控制表面（1; 11,14）特别是沿着跨度宽度方向（9）弹性变形，而不会扭结，在这种情况下，可以相对于侧面沿着控制表面实现均匀的过渡流动方向（6）。本发明使得可以减少由控制表面引起的涡流和噪声。

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