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公开(公告)号：US07395989B2
公开(公告)日：2008-07-08
申请号：US11311548
申请日：2005-12-20
申请人： Bruno Saint-Jalmes , André Rezag , Jason Zaneboni
发明人： Bruno Saint-Jalmes , André Rezag , Jason Zaneboni
IPC分类号： B64C1/20
CPC分类号： B64D11/00 , B64C2001/0036
摘要： An aircraft fuselage includes an outer skin and at least one main deck separating an interior space of the aircraft fuselage longitudinally into a first space and a second space. At least one portion of the first space is divided into at least three longitudinal zones, and the at least three longitudinal zones include at least one central zone and at least two lateral zones. The at least one central zone is divided into three sectors, and the three sectors include a front sector, a central sector, and a rear sector. The at least two lateral zones include a first and second lateral zone configuration, the front sector includes a first and second front sector configuration, the central sector includes a first and second central sector configuration, and the rear sector includes a first and second rear sector configuration.
摘要翻译： 飞机机身包括外皮和至少一个主甲板，其将飞机机身的内部空间纵向分成第一空间和第二空间。 第一空间的至少一部分被分成至少三个纵向区域，并且至少三个纵向区域包括至少一个中心区域和至少两个侧向区域。 至少一个中央区域分为三个部分，三个部分包括前部扇区，中央扇区和后部扇区。 所述至少两个横向区域包括第一和第二横向区域构造，所述前部区段包括第一和第二前部扇形结构，所述中央扇区包括第一和第二中央扇形结构，并且所述后部扇区包括第一和第二后部扇区 组态。
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公开(公告)号：US06047923A
公开(公告)日：2000-04-11
申请号：US372390
申请日：1995-01-13
申请人： Patrick A. Lafferty
发明人： Patrick A. Lafferty
CPC分类号： B64C1/10 , B64D11/00 , B64C2001/0036
摘要： An aircraft having a central fuselage, a first side fuselage positioned immediately adjacent to and independent of the central fuselage, and a second side fuselage positioned immediately adjacent to and independent of the central fuselage located on the opposite side of the first side fuselage is disclosed. All of the engines powering the aircraft are located either on the wings outboard of the side fuselages or in the rear of the aircraft aft of the wings. Further, the aircraft may include wings positioned laterally from both side fuselages which may be partially retracted during flight.
摘要翻译： 公开了一种具有中央机身的第一侧机身，与第一侧机身紧邻且独立于中央机身的第一机身以及紧邻第一侧机身相对侧并独立于中央机身定位的第二侧机身。 所有为飞机提供动力的发动机都位于机身外侧的机翼或机翼后方的机翼后方。 此外，飞机可以包括从两侧机身侧向设置的翼，其可以在飞行期间部分地缩回。
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公开(公告)号：US20100187352A1
公开(公告)日：2010-07-29
申请号：US12526784
申请日：2008-01-29
申请人： Michael Yavilevich
发明人： Michael Yavilevich
CPC分类号： B64C1/061 , B64C1/062 , B64C2001/0027 , B64C2001/0036 , B64C2001/0072 , B64D9/00 , B64D11/00 , B64D37/04 , Y02T50/43 , Y02T50/44 , Y02T50/46
摘要： The invention relates to multi deck passenger aircraft, having passenger cabins and/or service facilities arranged on the upper and lower deck and inner load bearing cell structure provided within aircraft body. The present invention is also directed toward methods for manufacturing derivative multi deck aircrafts. Energy absorbing, floatable cargo containers (24) attached to fuselage belly. External fuel tanks (26) displaced on the top of fuselage. Center wing region of the fuselage is using for arranging rows of seats and service facilities. Addition seating configuration for narrow and wide bodied aircraft is provided. Multi deck seating configuration significantly reduces per passenger operating cost over existing technology. Less fuel per passenger is required since there is less airframe weight and wetted area per passenger. Due to the lower overall cost per passenger seat within the multi deck seating structure, the net profit and return on investment in the aircraft are also increased.
摘要翻译： 本发明涉及多层乘客机，其具有布置在飞机机体内的上下甲板和内承重单元结构的客舱和/或服务设施。 本发明还涉及制造衍生多层飞机的方法。 能量吸收，可浮动的货物集装箱（24），附在机身的腹部。 外部燃料箱（26）在机身顶部移动。 机身的中心翼区域用于排列座椅和服务设施。 提供了狭窄和宽体积飞机的增加座椅配置。 多层座椅配置大大降低了乘客运营成本，超过现有技术。 需要较少的乘客燃料，因为每个乘客的机身重量和湿润面积较小。 由于多座位座椅结构中乘客座位的总体成本较低，飞机的净利润和投资回报率也有所增加。
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公开(公告)号：US20040129836A1
公开(公告)日：2004-07-08
申请号：US10605142
申请日：2003-09-10
申请人： THE BOEING COMPANY
发明人： Gerhard E. Seidel
IPC分类号： B64C001/00
CPC分类号： B64D27/02 , B64C1/00 , B64C2001/0036 , B64D37/04 , Y02T90/44
摘要： An aircraft powered with a non-hydrocarbon based fuel source, such as liquid hydrogen. The fuselage contains two elongated cylindrical-type sections positioned side-by-side and joined firmly together. One of the sections houses at least one fuel tank, while the other section can be used to transport passengers, freight and the like.
摘要翻译： 由非烃类燃料源（如液态氢）供电的飞机。 机身包含两个细长的圆柱形部分并排放置并牢固连接在一起。 其中一个部分至少装有一个燃料箱，而另一个部分可用于运输乘客，货运等。
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公开(公告)号：US06394392B1
公开(公告)日：2002-05-28
申请号：US09691930
申请日：2000-10-18
申请人： Patrick A. Lafferty
发明人： Patrick A. Lafferty
IPC分类号： B64C100
CPC分类号： B64C1/10 , B64C1/1415 , B64C2001/0036 , B64C2001/0045 , B64C2001/0072 , B64D7/08 , Y02T50/12 , Y02T50/43
摘要： The present invention relates to an aircraft having a plurality of fuselages for increased payload. More specifically, the aircraft has a central fuselage, and first and second side-saddle fuselages mounted on opposite sides of the central fuselage. The first and second side-saddle fuselages further are provided with a mechanism for opening and each of the side-saddle fuselages define a launch tube such that each launch tube is adapted for transporting and launching a large or oversize missile.
摘要翻译： 本发明涉及具有多个用于增加有效载荷的机身的飞行器。 更具体地说，飞机具有中央机身，第一和第二侧鞍机身安装在中央机身的相对两侧。 第一和第二侧鞍机身还设置有用于打开的机构，并且每个侧鞍机身限定发射管，使得每个发射管适于传送和发射大型或超大型导弹。
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公开(公告)号：US07318566B2
公开(公告)日：2008-01-15
申请号：US11233889
申请日：2005-09-23
IPC分类号： B64C1/22
CPC分类号： B66B9/02 , B64C1/22 , B64C2001/0027 , B64C2001/0036 , B64D9/00 , B64D11/0007 , B66B11/0206
摘要： An aircraft incorporates a lift system for guiding a lift cabin. The lift cabin 21 is capable of servicing several decks in the aircraft. A guiding structure is mounted inside the aircraft fuselage 1 by mounting it to the floor and deck structures, while allowing for strains between the floor and the deck in the vertical direction. The lift cabin is capable of travelling down to the ground if a door in the underside of the fuselage is provided. The lift cabin is arranged on the guiding structure using a bogie truck mounted on the lift cabin, and the bogie truck may be actively connected with profile rails of the guiding structure via roll blocks. The part of the bogie truck carrying the roll blocks or other guiding element may remain within the fuselage, when the cabin is positioned on the ground.
摘要翻译： 飞机包含一个用于引导电梯舱的电梯系统。 升降机舱21能够维修飞行器中的多个甲板。 引导结构通过将其安装在地板和甲板结构上而安装在飞行器机身1内，同时允许在地板和甲板之间在垂直方向上的应变。 如果提供机身下侧的门，电梯舱能够向下行进。 升降机舱使用安装在升降机舱上的转向架，布置在导向结构上，转向架可以通过滚动块主动地与引导结构的轮廓轨连接。 当机舱位于地面上时，携带滚动块或其他引导元件的转向架卡车的部分可能会保留在机身内。
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公开(公告)号：US20060214057A1
公开(公告)日：2006-09-28
申请号：US11311548
申请日：2005-12-20
申请人： Bruno Saint-Jalmes , Andre Rezag , Jason Zaneboni
发明人： Bruno Saint-Jalmes , Andre Rezag , Jason Zaneboni
CPC分类号： B64D11/00 , B64C2001/0036
摘要： This aircraft fuselage comprises an outer skin and at least one main deck defining an occupancy space. At least one portion of the occupancy space is divided into at least three longitudinal zones, at least one central zone and at least two lateral zones. The lateral zones are adapted to hold either seats for accommodating passengers, or freight. At least one central zone is adapted to hold freight over at least a portion of its length. At least one lateral zone comprises an aisle for the passage, in a transverse direction, of the freight placed in a central zone.
摘要翻译： 该飞机机身包括外皮和限定占用空间的至少一个主甲板。 占用空间的至少一部分被分成至少三个纵向区域，至少一个中心区域和至少两个横向区域。 侧面区域适于容纳用于容纳乘客的座位或货物。 至少一个中心区域适于在其长度的至少一部分上保持货物。 至少一个横向区域包括用于在横向方向上通过放置在中心区域中的货物的通道。
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公开(公告)号：US6123295A
公开(公告)日：2000-09-26
申请号：US9355
申请日：1998-01-20
CPC分类号： B64C1/0009 , B64C1/061 , B64C39/10 , B64D37/04 , B64D37/06 , B64G1/14 , B64G1/402 , B64C2001/0036 , B64C2001/0045 , B64C2001/0072 , Y02T50/433
摘要： An improved fuel tank for a lifting body re-entry vehicle having a particular external shape comprising four elongated lobes each having an external surface, each of the external surfaces having selected cylindrical and conical shapes, the lobes being selectively mateable to form a combined external configuration having a multiplicity of cylindrical and conical shapes conformable to at least a portion of the external shape of the vehicle. The cylindrical and conical shapes have variable radii at selected cross-sections thereof, such radii being selected for forming the external configuration. In a particular embodiment, the fuel tank has an initial portion, a midsection portion and a final portion and the cross-sectional shape of the initial portion of the fuel tank is that of two overlapping circles whose centers are positioned above one another, each of the circles being formed by two of the four lobes. In the midportion of the fuel tank, the cross-sectional shape is that of four overlapping circles whose centers are positioned to form a four-lobed closed arcuate figure. In the final portion of the fuel tank, the cross-sectional shape of the fuel tank is that of two overlapping circles whose centers are positioned aside one another, each of the circles being formed by two of the four lobes. When two such fuel tanks are placed side-by-side, the combined external surfaces closely approximate a large portion of the shape of the re-entry vehicle.
摘要翻译： 一种改进的用于具有特定外部形状的提升体再入式车辆的燃料箱，包括四个细长的凸角，每个细长的凸角具有外表面，每个外表面具有选定的圆柱形和圆锥形形状，凸角可选择地配合以形成组合的外部构型 具有与车辆的外部形状的至少一部分相适应的多个圆柱形和圆锥形状。 圆柱形和圆锥形的形状在其选定的横截面具有可变的半径，这种半径被选择用于形成外部构造。 在特定实施例中，燃料箱具有初始部分，中部部分和最终部分，并且燃料箱的初始部分的横截面形状是其中心彼此位于彼此之间的两个重叠圆的横截面形状 圆形由四个凸角中的两个形成。 在燃料箱的中间部分，横截面形状是四个重叠的圆的形状，其中心被定位成形成四裂的封闭弧形图。 在燃料箱的最后部分中，燃料箱的横截面形状是两个重叠的圆的中心彼此相对定位，每个圆由四个凸角中的两个形成。 当两个这样的燃料箱并排放置时，组合的外表面接近重返车辆形状的大部分。
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公开(公告)号：US5921593A
公开(公告)日：1999-07-13
申请号：US924003
申请日：1997-08-29
申请人： Heinz Gassert
发明人： Heinz Gassert
CPC分类号： B64C1/22 , B64C1/00 , B64C2001/0027 , B64C2001/0036 , Y10T292/1021
摘要： A movable tension tie assembly (10) for a fuselage of an airplane, includes a plurality of elongate struts (12a) and (12b) having a first end (16) and a second end (28) longitudinally spaced therefrom. The first end of each strut being swingingly connected to the interior of the fuselage for swinging movement of the struts between a retracted position, wherein the struts do not obstruct the interior of the fuselage, and an extended position, wherein the struts extend substantially across the diameter of the interior of the fuselage. The movable tension tie assembly also includes first and second lock assemblies (14a) and (14b) rigidly connected to the interior of the fuselage for locking engagement with the struts. The lock assemblies include a drive motor (17) operatively connected thereto for selectively actuating the locking assembly between a locked position wherein the struts are held in the extended position to limit deflections of the fuselage when the fuselage is pressurized and an unlocked position wherein the struts may be swung into the retracted position.
摘要翻译： 一种用于飞机机身的可移动张紧系统组件（10）包括多个细长支柱（12a）和（12b），其具有与其纵向间隔开的第一端（16）和第二端（28）。 每个支柱的第一端摆动地连接到机身内部，用于在缩回位置之间的支柱的摆动运动，其中支柱不会阻碍机身的内部和延伸位置，其中支柱基本上延伸穿过 机身内径的直径。 可移动张紧系统组件还包括刚性地连接到机身内部的用于与支柱锁定接合的第一和第二锁定组件（14a）和（14b）。 锁定组件包括可操作地连接到其上的驱动马达（17），用于在锁定位置之间选择性地启动锁定组件，其中支撑件保持在延伸位置，以限制当机身被加压时机身的偏转和解锁位置，其中支柱 可以摆动到缩回位置。
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公开(公告)号：US11932374B2
公开(公告)日：2024-03-19
申请号：US16672423
申请日：2019-11-01
申请人： The Boeing Company
CPC分类号： B64C1/22 , B64D9/00 , B65D88/121 , B65D88/14 , B65D90/0066 , B64C2001/0036 , B64C2001/0045 , B64C2025/008
摘要： A trunk route aircraft has at least one wing for supporting the aircraft during flight, and at least one propulsor for forward propulsion of the aircraft. The trunk route aircraft further includes a pressurized trunk route fuselage having a double-bubble cross-sectional shape and a generally vertically-oriented longitudinal bulkhead dividing the trunk route fuselage interior into two side-by-side trunk route payload compartments. The longitudinal bulkhead is loaded in tension when the trunk route fuselage is pressurized. The trunk route payload compartments are each configured to receive a plurality of lightweight ISO (International Organization for Standardization) geometry containers arranged end-to-end, or a plurality of container inserts arranged end-to-end, each container insert also configured to be received within the lightweight ISO-geometry container, or a combination of one or more lightweight ISO-geometry containers and one or more container inserts arranged end-to-end.
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