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公开(公告)号：US06478253B1
公开(公告)日：2002-11-12
申请号：US09839260
申请日：2001-04-20
申请人： Gerhard E. Seidel
发明人： Gerhard E. Seidel
IPC分类号： B64C100
CPC分类号： B64C1/00 , B64C2001/0027
摘要： An aircraft having a fuselage and a wing employs area-ruling of the fuselage in a vertical direction, with at least a substantial amount of the area-ruling being accomplished by dishing the keel area of the fuselage directly below the center portion of the wing. In one embodiment the aircraft has a main passenger seating deck and forward and aft upper seating decks located above the main deck respectively forward and aft of the wing, and both the upper surface of the fuselage above the wing and the lower surface of the fuselage below the wing are area-ruled.
摘要翻译： 具有机身和机翼的飞行器在垂直方向上使用机身的区域划线，至少通过将机身的龙骨区域直接在机翼的中心部分的下方进行凹陷来实现。 在一个实施例中，飞机具有主要乘客座椅甲板和位于主甲板上方的前甲板和后部上座椅甲板，分别在机翼的前方和后部以及机身上方的机身的上表面和机身的下表面以及机身的下表面 机翼是区域划分的。
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公开(公告)号：US5992797A
公开(公告)日：1999-11-30
申请号：US157086
申请日：1998-09-18
CPC分类号： B64C1/00 , B64D11/00 , B64C2001/0027 , B64C2001/0045 , Y02T50/12
摘要： An improvement to a subsonic passenger aircraft is provided. The passenger aircraft has a fuselage including a main passenger seating deck (14) including forward, middle, and aft regions. The fuselage includes an upper forward deck (16) located above the main passenger seating deck forward region and accessible thereto. Both the main deck and upper forward deck having doors (30), (26) therein for passenger and supplies ingress and egress. The fuselage includes an aft upper deck (18) located above the main passenger seating deck aft region and accessible from the main deck. An upper middle region (20) is located above the main deck middle region. In one embodiment, the upper middle region (20) is of a height elevationally less than either of the forward and aft upper decks. The cross-sectional area of the fuselage at the upper middle region is less than the cross-sectional area of the fuselage at either the forward upper deck region or the aft upper deck region. In another embodiment, the forward upper cabin and the aft upper cabin are separate, longitudinally non-adjacent cabins for accommodating seated passengers.
摘要翻译： 提供对亚音速客机的改进。 客机具有机身，其中包括一个主要乘客座椅甲板（14），包括前，中，后区域。 机身包括位于主乘客座椅甲板前方区域上方的上方前甲板（16），并可到达。 主甲板和上前甲板都有门（30），（26），用于乘客和进出口。 机身包括位于主乘客座甲板后部区域上方的后甲板（18），并可从主甲板进入。 上中部区域（20）位于主甲板中部区域上方。 在一个实施例中，上中间区域（20）的高度高度比前甲板和后甲板中的任何一个小。 上部中部区域的机身横截面面积小于前甲板区域或后甲板区域的机身横截面积。 在另一个实施例中，前部上部舱和后部舱室是分开的，纵向不相邻的舱室，用于容纳就座乘客。
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公开(公告)号：US4767270A
公开(公告)日：1988-08-30
申请号：US852652
申请日：1986-04-16
申请人： Gerhard E. Seidel
发明人： Gerhard E. Seidel
CPC分类号： B64C11/001 , B64C11/48 , F01D5/225 , F01D7/00 , F02K3/04 , F02K3/072 , B64D2027/005 , F05D2260/74 , F05D2260/76 , Y02T50/66 , Y02T50/672 , Y02T50/673
摘要： A fan jet engine assembly comprising a hoop fan surrounding a turbojet (19) is disclosed. The hoop fan includes a pair of rotatable hubs (27, 29) that encircle the turbojet. A stage of fan blades (31, 33) is attached to each hub (27, 29) and radiates outwardly therefrom. The tips of the blades (31, 33) of at least one of the stages attached to a loop (23/25 or 61) that encircles the tips of the blades (31, 33) of both stages. Due to the attachment of the hoop (23/25 or 61) to the blades (31, 33), the hoop rotates as the hubs (27, 29) are rotated by the turbojet (19). The pitch of the blades of at least one of the stages is adjustable.
摘要翻译： 公开了一种包括围绕涡轮喷气发动机（19）的环形风扇的风扇喷气发动机组件。 环形风扇包括环绕涡轮喷气的一对可旋转轮毂（27,29）。 风扇叶片（31,33）的阶段附接到每个轮毂（27,29）并从其向外辐射。 至少一个级的叶片（31,33）的尖端附接到环绕两级叶片（31,33）的尖端的环（23/25或61）。 由于箍（23/25或61）与叶片（31,33）的连接，当轮毂（27,29）由涡轮喷气机（19）旋转时，环转。 至少一个级的叶片的间距是可调节的。
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公开(公告)号：US4231481A
公开(公告)日：1980-11-04
申请号：US29607
申请日：1979-04-13
申请人： Gilbert J. Nash , Gerhard E. Seidel
发明人： Gilbert J. Nash , Gerhard E. Seidel
CPC分类号： B65D90/0046 , B65D88/128 , B65D90/0053 , B65D90/006 , B65D2590/005 , B65D2590/0058
摘要： An intermodal cargo container capable of being quickly and easily converted between a solid storage mode and a fluent storage mode is disclosed. Shell sections adapted to be either removed from, or pivoted within, an outer container are provided to support an impermeable liner in the fluent storage mode. Elements of both the inner and outer container may be of conventional construction for surface transport or of lightweight construction suitable for air as well as surface transport.
摘要翻译： 公开了能够在固体储存模式和流动储存模式之间快速且容易地转换的联运货物集装箱。 提供适于从外部容器中移出或枢转的外壳部分，以支持流体储存模式中的不可渗透的衬垫。 内容器和外容器的元件可以是用于表面输送或适于空气以及表面输送的轻质结构的常规结构。
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公开(公告)号：US06971609B2
公开(公告)日：2005-12-06
申请号：US10740952
申请日：2003-12-18
申请人： Gerhard E. Seidel
发明人： Gerhard E. Seidel
CPC分类号： B64C30/00 , B64D11/00 , B64D11/0601
摘要： An aircraft passenger seating arrangement has at least one passenger seat within an enclosure and an aisle located within the enclosure adjacent to the seat with no seats located adjacent to an opposite side of the aisle from the seat. The enclosure has a frame with a symmetrical cross section, the frame having a curved perimeter wherein the height of the cross section is different than the width to minimize cross sectional area of the aircraft body to reduce sonic boom signature.
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公开(公告)号：US06405975B1
公开(公告)日：2002-06-18
申请号：US09135992
申请日：1998-08-18
申请人： Mithra M. K. V. Sankrithi , David W. McKenna , Mannon L. Wallace, Jr. , Ronaldo O. Cabrera , Gary D. Reysa , Gerhard E. Seidel , John Yeeles , John Cashman
发明人： Mithra M. K. V. Sankrithi , David W. McKenna , Mannon L. Wallace, Jr. , Ronaldo O. Cabrera , Gary D. Reysa , Gerhard E. Seidel , John Yeeles , John Cashman
IPC分类号： B64C2550
摘要： A system for aiding ground maneuvering of an airplane. The system includes at least one camera mounted on the airplane for generating video images of at last one gear with tires, preferably a main or nose landing gear and the surrounding ground. The cockpit of the airplane includes a video display device that displays the generated video images and a user interface that allows selection of the format for displaying the generated video images. A camera mounted within a moveable component of the airplane is mounted on a movable device that compensates for component movement. The system also includes a display generator for generating in real-time superimposed oversteer targets on the displayed video images. The video images with oversteer targets assist the pilot in determining the airplane's actual position relative to runways, taxiways, obstacles and other ground features and to maneuver a plane with a wide wheel track long wheelbase, or both accordingly.
摘要翻译： 协助飞机的地面操纵的系统。 该系统包括安装在飞机上的至少一个照相机，用于产生最后一个齿轮的视频图像，轮胎，优选地是主起落架或前起落架和周围地面。 飞机的驾驶舱包括显示生成的视频图像的视频显示装置和允许选择用于显示所生成的视频图像的格式的用户界面。 安装在飞机的可移动部件内的相机安装在可补偿组件运动的可移动装置上。 该系统还包括用于在所显示的视频图像上实时叠加过度转向目标的显示发生器。 具有过度转向目标的视频图像有助于飞行员确定飞机相对于跑道，滑行道，障碍物和其他地面特征的实际位置，并且相应地操纵具有宽轮轨长轴距的平面。
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公开(公告)号：US4917334A
公开(公告)日：1990-04-17
申请号：US251428
申请日：1988-09-30
申请人： Harry C. Ralph , Gerhard E. Seidel
发明人： Harry C. Ralph , Gerhard E. Seidel
CPC分类号： B64C25/34
摘要： A multiwheel landing gear assembly includes a forward set of wheels which are in tandem with a middle set of wheels which in turn are in tandem with a rear set of wheels. The forward set of wheels are connected to a main support strut of the landing gear by a levered arrangement. The middle and rear set of wheels are connected together by a truck beam which in turn is connected to the main support strut by a radius rod. When the middle and rear wheels are subject to an upward force such as when the aircraft is landing, the radius rod limits movement of the wheels in a generally upward direction along a path having a radius which is equal to the length of the radius rod. Movement of the middle and rear wheels along the path in the upward direction is resisted by a shock absorber. In this manner, the vertical loads are reacted in a lengthwise direction along the radius rod and shock absorber.
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8.发明授权公开(公告)号：US08689538B2
公开(公告)日：2014-04-08
申请号：US12555812
申请日：2009-09-09
IPC分类号： F02K3/02
CPC分类号： F02K3/077 , B64C11/48 , B64D27/12 , B64D27/14 , B64D2027/005 , B64D2027/026 , F01D7/00 , F02K3/06 , F05D2220/324 , F05D2220/325 , F05D2260/96 , Y02T50/64 , Y02T50/66 , Y02T50/673
摘要： An ultra-efficient “green” aircraft propulsor utilizing an augmentor fan is disclosed. A balanced design is provided combining a fuel efficient and low-noise high bypass ratio augmentor fan and a low-noise shrouded high bypass ratio turbofan. Three mass flow streams are utilized to reduce propulsor specific fuel consumption and increase performance relative to conventional turbofans. Methods are provided for optimization of fuel efficiency, power, and noise by varying mass flow ratios of the three mass flow streams. Methods are also provided for integration of external propellers into turbofan machinery.
摘要翻译： 公开了一种使用增压风扇的超高效“绿色”飞机推进器。 提供了平衡的设计，结合了燃油效率和低噪声高旁路比增强器风扇和低噪声罩高旁通比涡轮风扇。 利用三个质量流量来相对于常规涡轮风扇减少推进剂特定的燃料消耗并提高性能。 提供了通过改变三个质量流量的质量流量比来优化燃料效率，功率和噪声的方法。 还提供了将外部螺旋桨整合到涡轮风扇机械中的方法。
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公开(公告)号：US06293497B1
公开(公告)日：2001-09-25
申请号：US09284122
申请日：1999-04-05
IPC分类号： B64C314
摘要： Slotted cruise airfoil technology allows production of a substantially unswept wing that achieves the same cruise speed as today's conventional jet airplanes with higher sweep. This technology allows the wing boundary layer to negotiate a strong recovery gradient closer to the wing trailing edge. The result is about a cruise speed of Mach=0.78, but with a straight wing. It also means that for the same lift, the super velocities over the top of the wing can be lower. With very low sweep and this type of cruise pressure distribution, natural laminar flow will be obtained. In addition, heat is transferred from the leading edge of the wing and of the main flap to increase the extent of the natural laminar flow. The slotted cruise wing airfoil allows modularization of the wing and the body for a family of airplanes. The unsweeping of the wing significantly changes the manufacturing processes, reduces manufacturing costs and flow time from detail part fabrication to airplane delivery. The system architecture is all new for cost reduction. A high wing arrangement allows more freedom for installation of higher bypass ratio advanced geared fan engines. A low is wing in conjunction with aft body mounted engines will have a similar effect. Aerodynamic efficiency and engine fuel burn efficiency result in considerable lower emission of noise and greenhouse gases.
摘要翻译： 开槽的巡航翼型技术可以生产一个基本上没有刮过的机翼，可以实现与现在更高扫描速度的传统喷气式飞机相同的巡航速度。 该技术允许机翼边界层协调一个更靠近机翼后缘的强恢复梯度。 结果是马赫= 0.78的巡航速度，但是有一个直翼。 这也意味着对于相同的升力，机翼顶部的超速度可以更低。 通过非常低的扫描和这种类型的巡航压力分布，将获得自然层流。 此外，热量从机翼和主翼片的前缘传递，以增加自然层流的程度。 开槽的巡航翼型机翼允许机翼和车身的模块化用于一系列飞机。 机翼的不知不觉中显着改变了制造过程，降低了制造成本，并将流程从细节部件制造到飞机交付。 系统架构全新的降低成本。 高翼安排允许更多的自由安装更高旁路比的先进的齿轮风扇发动机。 一个低的翼与后身体搭配的发动机将具有相似的效果。 空气动力学效率和发动机燃料燃烧效率导致噪音和温室气体排放量相当低。
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公开(公告)号：USD504862S1
公开(公告)日：2005-05-10
申请号：US29189739
申请日：2003-09-10
申请人： Gerhard E. Seidel
设计人： Gerhard E. Seidel
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