专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US06834833B2 Twin aisle small airplane 有权
标题翻译：双通道小飞机
公开(公告)号：US06834833B2
公开(公告)日：2004-12-28
申请号：US09969801
申请日：2001-10-02
申请人： Mithra M. K. V. Sankrithi
发明人： Mithra M. K. V. Sankrithi
IPC分类号： B64C100
CPC分类号： B64C1/00 , B64C2001/0045 , B64D1/10 , B64D11/00 , B64D11/0601 , Y02T50/12
摘要： A less-than-200-seat-class passenger airplane includes a passenger cabin with two longitudinal aisles, and at least six economy class seats abreast the cabin. The cross-section of the cabin perpendicular to a longitudinal axis of the airplane fuselage has a horizontal diameter value in excess of a vertical diameter value.
摘要翻译：一个不到200个座位的乘客飞机包括一个带有两个纵向通道的乘客舱，以及至少六个经济舱座椅。垂直于飞机机身纵轴的机舱横截面的水平直径值超过垂直直径值。

2. 发明授权

US06802479B2 Flammable fluid line shroud 有权
标题翻译：易燃液体导管护罩
公开(公告)号：US06802479B2
公开(公告)日：2004-10-12
申请号：US10147392
申请日：2002-05-16
申请人： Mark E. Howe , Kevin L. Loss , B. Kelly Sheahan
发明人： Mark E. Howe , Kevin L. Loss , B. Kelly Sheahan
IPC分类号： B64C100
CPC分类号： F02C7/222 , B64D37/00 , F05D2260/602 , Y02T50/672
摘要： A method and apparatus contains and drains leakage from fluid system piping on a mobile platform such as an aircraft. A generally U-shaped channel is formed having outwardly oriented edge flanges and either integral or attached end plates. A pair of drain connections is disposed adjacent to each end plate. A group of fluid lines including at least one flammable fluid line is loaded within the U-shaped channel. A cover plate having outwardly oriented edge flanges aligning with the U-shaped channel edge flanges is positioned over the U-shaped channel. The edge flanges of both the cover plate and the U-shaped channel are joined with a seal such that a fluid-tight assembly results. Fluid leakage from any of the group of enclosed fluid lines discharges through the pair of drain connections. One of the end plates forms a firewall connectable to an engine firewall boundary.
摘要翻译：一种方法和装置包含并排出诸如飞机的移动平台上的流体系统管道的泄漏。大致U形通道形成有向外定向的边缘凸缘和整体或附接的端板。一对排水连接设置在每个端板附近。包括至少一个易燃流体管线的一组流体管线被装载在U形通道内。具有与U形通道边缘凸缘对准的向外定向的边缘凸缘的盖板位于U形通道上。盖板和U形通道的边缘凸缘与密封件接合，从而得到流体密封的组件。来自任何一组封闭流体管线的流体泄漏通过一对排水连接排放。其中一个端板形成可连接到发动机防火墙边界的防火墙。

3. 发明授权

US06705567B2 Tandem wing aircraft and method for manufacturing and operating such aircraft 失效
标题翻译：串联翼飞机和制造和操作这种飞机的方法
公开(公告)号：US06705567B2
公开(公告)日：2004-03-16
申请号：US10140200
申请日：2002-05-06
申请人： Lawrence Y. Dong , Mithra M. K. V. Sankrithi
发明人： Lawrence Y. Dong , Mithra M. K. V. Sankrithi
IPC分类号： B64C100
CPC分类号： B64C39/12 , B64C30/00 , B64C2001/0027 , B64D11/00
摘要： An aircraft and associated method of manufacture and operation. The aircraft can include a fuselage having a first portion and a second portion projecting upwardly from the first portion, with the first portion housing a passenger deck and the second portion being positioned above the passenger deck. A first wing can extend outwardly from the first portion of the fuselage and the second wing can extend outwardly from the second portion of the fuselage, with the second wing being positioned above and forward of the first wing. Accordingly, the fuselage can include a plurality of passenger doors simultaneously accessible to ground-based passenger load/unload equipment with at least one of the passenger doors positioned beneath the second wing.
摘要翻译：飞机及相关的制造和操作方法。飞机可以包括具有第一部分的机身和从第一部分向上突出的第二部分，其中第一部分容纳乘客甲板，第二部分位于乘客甲板上方。第一翼可以从机身的第一部分向外延伸，并且第二翼可以从机身的第二部分向外延伸，第二翼位于第一翼的上方和前方。因此，机身可以包括多个乘客门，其同时可接地的乘客负载/卸载设备，其中至少一个乘客门位于第二机翼的下方。

4. 发明授权

US06655635B2 Aircraft with ventral fairing and seal for such an aircraft 有权
标题翻译：具有腹部整流罩和这种飞机的密封的飞机
公开(公告)号：US06655635B2
公开(公告)日：2003-12-02
申请号：US10212065
申请日：2002-08-06
申请人： Jean-Pierre Maury , Alain Milhau , Bernard Pauly
发明人： Jean-Pierre Maury , Alain Milhau , Bernard Pauly
IPC分类号： B64C100
CPC分类号： F16J15/027
摘要： An aircraft includes a fuselage and a fixed flying surface having two wings, and a cradle-shaped ventral fairing at the crossover of the latter with the flying surface and provided with two longitudinal flanges climbing laterally along the fuselage and being provided with an opening for the passage with play of the corresponding wing to form a first peripheral slot around the ventral fairing and a second peripheral slot around each wing. An elongate seal is fixed to the periphery of the ventral fairing and to the periphery of each opening, so at to shut off the first and second slots, respectively. The seal includes a longitudinal elastic end lip applied, via the inner face of its free end, respectively against the fuselage or the flying surface and a longitudinal leaktightness member, carried by the inner face of the seal set back with respect to the end lip and also able to be applied against the fuselage or flying surface, respectively. The additional longitudinal leaktightness member is radially elastic bead.
摘要翻译：飞机包括机身和具有两个翼的固定飞行表面，以及在后者与飞行表面交叉处的摇篮式腹侧整流罩，并且设置有沿着机身横向攀升的两个纵向凸缘，并且设置有用于通过相应翼的游隙形成围绕腹侧整流罩的第一周边狭槽和围绕每个翼的第二周边槽。细长的密封件固定到腹侧整流罩的周边并且固定到每个开口的周边，从而分别关闭第一和第二狭槽。密封件包括纵向弹性端唇，其经由其自由端的内表面分别抵靠机身或飞行表面，以及纵向密封构件，其由密封件的内表面相对于端部唇缘背靠背承载，也可以分别应用于机身或飞行表面。附加的纵向密封件是径向弹性的珠。

5. 发明授权

US06626401B2 Aft fuselage control system for forward lifting elevator aircraft 失效
公开(公告)号：US06626401B2
公开(公告)日：2003-09-30
申请号：US10120055
申请日：2002-04-09
申请人： Norman Thomas Laurence Fraser
发明人： Norman Thomas Laurence Fraser
IPC分类号： B64C100
CPC分类号： B64C9/02 , B64C9/36
摘要： A system providing aft fuselage flight controls on forward lifting elevator aircraft. My invention relates to aft fuselage controls on a forward lifting elevator aircraft, with the main lifting wing placed aft on the fuselage, and equipped with trailing edge flaps. My embodiment includes a means for controlling a nose down pitching condition produced by lowering trailing edge flaps, using aft vertical flaps 2. The design of the aft vertical flaps 2 produces a tail-down moment to counter the main aft wing trailing edge flap action. In addition, the aft vertical flaps 2 add drag to the aircraft when deployed.

6. 发明授权

US06543721B2 Stressed-skin component made of metal 失效
标题翻译：由金属制成的强化皮肤组件
公开(公告)号：US06543721B2
公开(公告)日：2003-04-08
申请号：US09774091
申请日：2001-01-31
申请人： Frank Palm
发明人： Frank Palm
IPC分类号： B64C100
CPC分类号： B64C1/12 , B21C23/142
摘要： A stressed-skin component is made of metal including a skinplate and integrated stiffening profiles, which skin component apart from the required rigidity also provides adequate crack advance behaviour and retained strength behaviour. The stiffening profiles in the base area comprise a thicker region of a profile base thickness; the thicker region having a reduced connection thickness at the connection with the skinplate. The profile base thickness is at least twice the connection thickness.
摘要翻译：应力皮肤部件由金属制成，包括皮肤板和集成的加强型材，除了所需的刚性之外，皮肤部件还提供足够的裂纹提前行为和保持的强度行为。基部区域中的加强型材包括型材基底厚度较厚的区域; 较厚的区域在与皮肤板的连接处具有减小的连接厚度。轮廓基底厚度至少是连接厚度的两倍。

7. 发明授权

US06513757B1 Wing of composite material and method of fabricating the same 失效
标题翻译：复合材料翼及其制造方法
公开(公告)号：US06513757B1
公开(公告)日：2003-02-04
申请号：US09616399
申请日：2000-07-14
申请人： Kazuaki Amaoka , Takayuki Nagao , Atsushi Harada , Naoya Takizawa , Hideyuki Sano , Yasuhiro Toi , Megumi Hiraki
发明人： Kazuaki Amaoka , Takayuki Nagao , Atsushi Harada , Naoya Takizawa , Hideyuki Sano , Yasuhiro Toi , Megumi Hiraki
IPC分类号： B64C100
CPC分类号： B64C3/00 , B64F5/10 , Y10T428/24174 , Y10T428/24273 , Y10T428/24289
摘要： A wing of composite material has an upper skin, a lower skin and a plurality of intermediate spars arranged between the upper and the lower skin. The intermediate spars extend from roots to tips of the upper and the lower skins. The intermediate spars are integrally formed with the upper and the lower skins or are adhesively bonded to the upper and the lower skins. The wing has a small number of parts, needs greatly reduced time for fabrication and can be fabricated at a low cost.
摘要翻译：复合材料的翼片具有上皮肤，下皮肤和布置在上皮肤和下皮肤之间的多个中间翼片。中间翼梁从根部延伸到上部和下部皮肤的尖端。中间翼梁与上下皮一体地形成，或者粘合到上下皮上。机翼具有少量零件，需要大大缩短制造时间，并可以低成本制造。

8. 发明授权

US06386482B1 Detection apparatus 失效
标题翻译：检测装置
公开(公告)号：US06386482B1
公开(公告)日：2002-05-14
申请号：US09505535
申请日：2000-02-17
申请人： Richard S Capewell
发明人： Richard S Capewell
IPC分类号： B64C100
CPC分类号： B64D45/0005 , B64D2045/001
摘要： A detection apparatus for use with a system having a plurality of moveable surfaces, the apparatus comprising a signal transmission apparatus extending across each surface, a signal generator and a signal receiver. The apparatus further comprises a signal interrupter associated with adjacent ones of the surfaces and arranged to interrupt the transmission of a signal along the signal transmission apparatus upon relative movement of the adjacent ones of the surfaces occurring. The invention also relates to a leading edge high lift system of an aircraft wing having a plurality of moveable leading edge high lift surfaces.
摘要翻译：一种用于具有多个可移动表面的系统的检测装置，该装置包括跨越每个表面延伸的信号传输装置，信号发生器和信号接收器。该装置还包括与相邻表面相关联的信号中断器，并且被布置成在所发生的相邻表面的相对运动时中断沿着信号传输装置的信号的传输。本发明还涉及一种具有多个可移动的前缘高升力表面的飞机机翼的前缘高升力系统。

9. 发明授权

US06364250B1 Shell component for an aircraft fuselage and method of manufacturing the same 有权
标题翻译：用于飞机机身的壳体组件及其制造方法
公开(公告)号：US06364250B1
公开(公告)日：2002-04-02
申请号：US09406463
申请日：1999-09-27
申请人： Peter Brinck , Wilfried Mueller , Klaus P. Sanmann , Joerg Spitzner
发明人： Peter Brinck , Wilfried Mueller , Klaus P. Sanmann , Joerg Spitzner
IPC分类号： B64C100
CPC分类号： B64C1/12
摘要： A shell component for an aircraft fuselage includes a fuselage skin panel, a plurality of stringers extending in an aircraft lengthwise direction, and a plurality of frames extending crosswise relative to the stringers. The stringers and the frames are respectively welded onto the skin panel with the addition of a weld filler material. Each frame includes a frame root portion and a frame profile portion connected to each other. The frame root portion has cut-out notches receiving the stringers passing therethrough. The frame root portion is welded to the skin panel at the areas between the cut-out notches, and may be welded to the respective stringer in each cut-out notch. The stringers and frames are fabricated from webs and flanges, whereby a premanufactured grid of flanges may be used. The result is a very strong, yet simple shell component structure, that may be manufactured with a simple welding process, at a low cost and with low effort.
摘要翻译：用于飞行器机身的壳体部件包括机身蒙皮板，在飞行器长度方向上延伸的多个纵梁以及相对于纵梁横向延伸的多个框架。桁条和框架分别通过添加焊接填充材料焊接到皮肤面板上。每个框架包括彼此连接的框架根部部分和框架轮廓部分。框架根部具有接收穿过其中的桁条的切口凹口。框架根部在切口凹口之间的区域处焊接到皮肤面板，并且可以在每个切口凹口中焊接到相应的纵梁。桁条和框架由网和法兰制成，由此可以使用预制的法兰格。结果是非常坚固但简单的壳部件结构，其可以以低成本和低功耗以简单的焊接工艺制造。

10. 发明授权

US06778884B2 System and method for generating consolidated gas turbine control tables 失效
标题翻译：用于生成合并燃气轮机控制台的系统和方法
公开(公告)号：US06778884B2
公开(公告)日：2004-08-17
申请号：US10170524
申请日：2002-06-11
申请人： Gregory J. Chapman , John J. Rushinsky
发明人： Gregory J. Chapman , John J. Rushinsky
IPC分类号： B64C100
CPC分类号： F02C9/28 , F05D2270/053 , F05D2270/303 , F05D2270/708 , F05D2270/71
摘要： A method for generating a power setting parameter table. The method includes the steps of generating an index from a plurality of first and second inputs and determining a power setting parameter corresponding to each index and second input. The first inputs may include flight speed and temperature values and the second inputs may include altitude values.
摘要翻译：一种用于产生功率设置参数表的方法。该方法包括以下步骤：从多个第一和第二输入产生索引，并确定对应于每个索引和第二输入的功率设置参数。第一输入可以包括飞行速度和温度值，第二输入可以包括高度值。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式