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公开(公告)号：US20160297510A1
公开(公告)日：2016-10-13
申请号：US15089675
申请日：2016-04-04
摘要： An aircraft rear structure comprising a substantially flat rear pressure bulkhead, with a first side and a second side, opposite to the first side. The aircraft rear structure also comprises a horizontal stabilizer and a vertical stabilizer which in turn comprises a first spar and a second spar. The first spar is attached to a first attachment zone of the second side of the rear pressure bulkhead via first attaching elements, and the second spar is attached to a second attachment zone of the second side of the rear pressure bulkhead via second attaching elements. The second attachment zone being different from the first attachment zone.
摘要翻译： 一种飞机后部结构，包括基本上平坦的后部压力隔板，其具有与第一侧相对的第一侧和第二侧。 飞行器后部结构还包括水平稳定器和垂直稳定器，其又包括第一翼梁和第二翼梁。 第一翼梁经由第一附接元件附接到后压舱壁的第二侧的第一附接区域，并且第二翼梁经由第二附接元件附接到后压舱壁的第二侧的第二附接区域。 第二附接区域与第一附接区域不同。
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公开(公告)号：US20160107741A1
公开(公告)日：2016-04-21
申请号：US14976988
申请日：2015-12-21
申请人： The Boeing Company
发明人： Bruce Raymond Detert
CPC分类号： B64C5/02 , B64C1/00 , B64C1/0009 , B64C5/06 , B64C2001/0045 , B64F5/10
摘要： Aircraft fuselages are disclosed herein. An example apparatus includes a fuselage of an aircraft having a first section and a second section to which a tail assembly is to be coupled. The second section is aft of the first section and is to extend to at least a trailing edge of a horizontal stabilizer of the tail assembly. A first width of the first section decreases from a front to a rear of the first section, and a second width of the second section is substantially constant.
摘要翻译： 本文公开了飞机机身。 一种示例性装置包括具有第一部分的飞行器的机身和尾部组件将要连接到的第二部分。 第二部分是第一部分的后部，并且延伸到尾部组件的水平稳定器的至少后缘。 第一部分的第一宽度从第一部分的前部到后部减小，并且第二部分的第二宽度基本上是恒定的。
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公开(公告)号：US09284039B2
公开(公告)日：2016-03-15
申请号：US13891345
申请日：2013-05-10
发明人： Christian Maenz
摘要： A rudder system for an aircraft includes a center box, a rudder and actuators, wherein the rudder is pivoted around a hinge line relative to the center box. The actuators are arranged at an acute angle relative to the hinge line, and connected with at least one pivoted pivot lever, wherein the pivot lever is fastened to the rudder by way of a first push rod. This provides considerably more installation space in a vertical stabilizer of an aircraft for a center box, so that the latter can comprise a distinctly smaller wall thickness than usual in prior art to absorb air load-induced torsion and bending stresses.
摘要翻译： 用于飞行器的方向舵系统包括中心箱，方向舵和致动器，其中舵相对于中心箱围绕铰链线枢转。 致动器相对于铰链线成锐角设置，并且与至少一个枢转的枢转杆连接，其中枢转杆通过第一推杆固定到舵上。 这在中心箱的飞机的垂直稳定器中提供了相当多的安装空间，使得后者可以包括比现有技术中相对于吸收空气负载引起的扭转和弯曲应力明显更小的壁厚度。
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公开(公告)号：US09272773B2
公开(公告)日：2016-03-01
申请号：US14036992
申请日：2013-09-25
申请人： The Boeing Company
发明人： Rick A. Biedscheid
CPC分类号： B64C21/06 , B64C5/06 , B64C21/04 , B64C21/08 , B64C2230/04 , B64C2230/06 , B64D47/08 , Y02T50/166
摘要： Apparatus and methods to operate laminar flow control system doors are described. One described example apparatus includes an outboard structure of an aircraft, a first door assembly on a first side of the outboard structure having a first door defining a first opening and a second door assembly on a second side of the outboard structure having a second door defining a second opening. The example apparatus also includes a perforated surface proximate a leading edge of the outboard structure and an actuator disposed in the aircraft. The actuator drives first and second linkages that couple the first and second doors to the actuator. The first and second linkages are to operate the first and second doors, respectively, in an open mode in which the first and second openings create an airflow path between the perforated surface and the first and second openings.
摘要翻译： 描述了操作层流控制系统门的装置和方法。 一种描述的示例性设备包括飞行器的外侧结构，在外侧结构的第一侧上的第一门组件具有限定第一开口的第一门和在外侧结构的第二侧上的第二门组件，其具有限定 第二个开口 示例性装置还包括靠近外侧结构的前缘的穿孔表面和设置在飞行器中的致动器。 致动器驱动将第一和第二门连接到致动器的第一和第二连杆。 第一和第二连杆分别以打开模式操作第一和第二门，其中第一和第二开口在穿孔表面和第一和第二开口之间形成气流路径。
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公开(公告)号：US09228815B2
公开(公告)日：2016-01-05
申请号：US13542635
申请日：2012-07-05
摘要： An actuator including: a housing; a piston movably disposed in the housing, the piston being movable between an extended and retracted position; a plurality of gas generation charges generating a gas in fluid communication with the housing; and an exhaust port for exhausting gas from the cylinder generated by the plurality of gas generation charges; wherein activation of each of the plurality of gas generation charges results in an increase in pressure in the housing causing the piston to move in the housing from the refracted to the extended position. The actuator can further include a return spring for biasing the piston in the retracted position and the plurality of gas generation charges can be disposed in the housing.
摘要翻译： 一种致动器，包括：壳体; 可移动地设置在所述壳体中的活塞，所述活塞可在延伸和缩回位置之间移动; 产生与壳体流体连通的气体的多个气体发生装置; 以及用于从所述多个气体发生装置产生的从所述气缸排出气体的排气口; 其中多个气体产生装置中的每一个的致动导致壳体中的压力增加，使得活塞在壳体中从折射到延伸位置移动。 致动器还可以包括用于将活塞偏压在缩回位置的复位弹簧，并且多个气体发生装置可以设置在壳体中。
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公开(公告)号：US09216807B2
公开(公告)日：2015-12-22
申请号：US13659180
申请日：2012-10-24
申请人： The Boeing Company
发明人： Bruce Raymond Detert
CPC分类号： B64C5/02 , B64C1/00 , B64C1/0009 , B64C5/06 , B64C2001/0045 , B64F5/10
摘要： Aircraft fuselages are disclosed herein. An example apparatus includes a fuselage of an aircraft having a first section and a second section to which a tail assembly is to be coupled. The second section is aft of the first section and is to extend to at least a trailing edge of a horizontal stabilizer of the tail assembly. A first width of the first section decreases from a front to a rear of the first section, and a second width of the second section is substantially constant.
摘要翻译： 本文公开了飞机机身。 一种示例性装置包括具有第一部分的飞行器的机身和尾部组件将要连接到的第二部分。 第二部分是第一部分的后部，并且延伸到尾部组件的水平稳定器的至少后缘。 第一部分的第一宽度从第一部分的前部到后部减小，并且第二部分的第二宽度基本上是恒定的。
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17.发明授权Method for improving the aerodynamic efficiency of the vertical tail of an aircraft 有权提高飞机垂直尾翼空气动力学效率的方法公开(公告)号：US08783606B2
公开(公告)日：2014-07-22
申请号：US13439341
申请日：2012-04-04
申请人： Alain Tanguy
发明人： Alain Tanguy
CPC分类号： B64C5/06 , B64C9/00 , B64C2003/147 , Y02T50/12
摘要： A method for improving the aerodynamic efficiency of the vertical tail of an aircraft includes varying the thickness of the trailing edge of the rudder as a function of the span of the vertical tail. This variation is intended to adapt the local value of the coefficient of lateral lift applied to the vertical tail closer to a maximum allowable value. The maximum allowable value is specifically the value at which a separation of the aerodynamic flow is observed on the surface of the vertical tail.
摘要翻译： 用于改善飞行器的垂直尾翼的空气动力学效率的方法包括根据垂直尾翼的跨度改变舵的后缘的厚度。 该变化旨在使施加到垂直尾翼的横向升力系数的局部值更接近最大允许值。 最大允许值特别是在垂直尾部的表面上观察到空气动力流的分离的值。
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公开(公告)号：US08602356B2
公开(公告)日：2013-12-10
申请号：US11990578
申请日：2006-08-17
申请人： Christian Maenz
发明人： Christian Maenz
IPC分类号： B64C3/22
摘要： A wing box for an aircraft wing with a framework and a first shell. The framework is connected to the first shell such that a load acting on the first shell can be transferred by the framework.
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公开(公告)号：US20130320137A1
公开(公告)日：2013-12-05
申请号：US13891345
申请日：2013-05-10
发明人： Christian Maenz
IPC分类号： B64C9/02
摘要： A rudder system for an aircraft includes a centre box, a rudder and actuators, wherein the rudder is pivoted around a hinge line relative to the centre box. The actuators are arranged at an acute angle relative to the hinge line, and connected with at least one pivoted pivot lever, wherein the pivot lever is fastened to the rudder by way of a first push rod. This provides considerably more installation space in a vertical stabilizer of an aircraft for a centre box, so that the latter can comprise a distinctly smaller wall thickness than usual in prior art to absorb air load-induced torsion and bending stresses.
摘要翻译： 用于飞行器的方向舵系统包括中心箱，方向舵和致动器，其中舵相对于中心箱围绕铰链线枢转。 致动器相对于铰链线成锐角设置，并且与至少一个枢转的枢转杆连接，其中枢转杆通过第一推杆固定到舵上。 这在中心箱的飞机的垂直稳定器中提供了相当多的安装空间，使得后者可以包括比现有技术中相对于吸收空气负载引起的扭转和弯曲应力明显更小的壁厚度。
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公开(公告)号：US08104709B2
公开(公告)日：2012-01-31
申请号：US11989350
申请日：2006-05-11
申请人： Christian Mänz
发明人： Christian Mänz
CPC分类号： B64C1/26 , B64C5/06 , F16B5/025 , Y10T403/75
摘要： A lateral force joint, with which a plate-like spar can be fastened to a fuselage strap mounted on an airplane fuselage. The plate-like spar has a through bore, into which a fastening cylinder mounted on the flange can be inserted for connecting both components. In order to allow for the location of the spar to be adjusted with respect to the fuselage strap, a bearing bush of the spar is eccentrically fitted into the through bore. Correspondingly, the fastening cylinder of the fuselage strap is mounted eccentrically on a bearing bush so that a rotation of the bearing bushes allows the lateral force joint to be adjusted.
摘要翻译： 侧向力接头，板状翼梁可以固定在安装在飞机机身上的机身皮带上。 板状翼梁具有通孔，可以插入安装在凸缘上的紧固圆柱体以连接两个部件。 为了允许相对于机身带调节翼梁的位置，翼梁的轴承衬套偏心地装配到通孔中。 相应地，机身带的紧固圆柱体偏心地安装在轴承衬套上，使得轴承衬套的旋转允许侧向力接头被调整。
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