公开(公告)号：US06708924B2

公开(公告)日：2004-03-23

申请号：US10437763

申请日：2003-05-14

申请人： Mark A. Page ,  Jennifer P. Whitlock ,  Matthew W. Wilks

发明人： Mark A. Page ,  Jennifer P. Whitlock ,  Matthew W. Wilks

IPC分类号： B64C300

CPC分类号： B64C1/0009 ,  B64C39/10 ,  B64C2039/105 ,  B64C2211/00

摘要： A blended wing body aircraft having a modular body having a body that includes a plurality of laterally-extending body structures. Changes to the cargo capacity of the aircraft is accomplished through the employment of body structures that are wider or narrower. Configuration in this manner provides the aircraft with a structure that is relatively strong and efficient. While the body structures of this embodiment are not shared across a family of variously sized aircraft, the base design of the body structures is readily modifiable to adjust for an increase or decrease in width associated with a desired change to the aircraft's cargo capacity.

摘要翻译： 具有模块主体的混合翼体飞机具有包括多个横向延伸的主体结构的主体。 通过使用更宽或更窄的身体结构，可以改变飞机的货物能力。 以这种方式进行的配置为飞机提供了相对较强和高效的结构。 虽然该实施例的车身结构不是在不同尺寸的飞机系列之间共享，但是主体结构的基本设计是容易地可修改的，以适应与飞机货物容量的期望变化相关联的宽度的增加或减少。

公开(公告)号：US20040035098A1

公开(公告)日：2004-02-26

申请号：US10207796

申请日：2002-07-31

发明人： Karim El Hamel ,  Arnold C. Newton

IPC分类号： F02K003/00 ,  F02K007/00 ,  F02K009/00 ,  F02K009/74 ,  F02K009/76 ,  F02K011/00 ,  F02K009/78

CPC分类号： B64C11/001 ,  B64C39/10 ,  B64C2039/105 ,  B64D27/10 ,  B64D27/12 ,  B64D27/14

摘要： An engine arrangement (14) comprises a gas turbine engine unit (16) and first and second support members (18, 20). The support members (18, 20) extend from a structural component (24) of the engine casing (22) to support the engine unit in a position spaced from the body or airframe of the aircraft.

摘要翻译： 发动机装置（14）包括燃气涡轮发动机单元（16）和第一和第二支撑构件（18,20）。 支撑构件（18,20）从发动机壳体（22）的结构部件（24）延伸，以将发动机单元支撑在与飞行器的主体或机身间隔开的位置。

公开(公告)号：US20040031881A1

公开(公告)日：2004-02-19

申请号：US10399150

申请日：2003-04-14

发明人： Stephan Grigoryevich Jamgarov

IPC分类号： B64C001/00 ,  B64D001/00

CPC分类号： B64C39/10 ,  B64C1/00 ,  B64C2001/0045 ,  Y02T50/12

摘要： The invention relates to aircrafts, in particular to aircrafts, which are embodied in a passenger, cargo or cargopassenger variants thereby making it possible to improve performance characteristics by improving the aerodynamic properties thereof. The inventive aircraft having a carrying fuselage comprises a wing, an engine, and a fuselage whose width considerably exceeds the height thereof. A lower surface of the basic and the tail parts of the fuselage have a caved-in form in a cross-section thereof. A lower surface of the flattened front part of the fuselage is arranged at an attack angle with respect to the longitudinal horizontal plane of the aircraft. In addition, the front part of the aircraft has a curvilinear form in the plan view, which successively passes from the narrow front part to the basic large part of the fuselage. A tail group is embodied in the form of a double tail fins which are mutually spaced at a distance of the fuselage width with respect to the longitudinal vertical plane of the aircraft and are mounted at an angle with respect to said vertical plane of the aircraft.

摘要翻译： 本发明涉及飞机，特别是涉及飞机，其体现在乘客，货物或卡车乘客变体中，从而可以通过改善其空气动力特性来改善性能特征。 具有携带机体的本发明飞行器包括机翼，发动机和其宽度显着超过其高度的机身。 机身的基部和尾部的下表面在其横截面上具有塌陷形式。 机身平整的前部的下表面相对于飞行器的纵向水平面以攻角设置。 此外，飞机的前部在平面图中具有曲线形式，从机身的窄前部到基本大部分依次通过。 尾部组件以双尾翼片的形式被体现，该双尾翼片相对于飞行器的纵向垂直平面在机身宽度的距离处相互间隔开并且相对于飞行器的所述垂直平面以一定角度安装。

公开(公告)号：US20030197097A1

公开(公告)日：2003-10-23

申请号：US08917480

申请日：1997-08-26

发明人： SEAN R. WAKAYAMA

IPC分类号： B64C003/50

CPC分类号： B64C39/10 ,  B64C3/10 ,  B64C9/12 ,  B64C2039/105 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44

摘要： Independently deflectable control surfaces are located on the trailing edge of the wing of a blended wing-body aircraft. The reconfiguration control system of the present invention controls the deflection of each control surface to optimize the spanwise lift distribution across the wing for each of several flight conditions, e.g., cruise, pitch maneuver, and high lift at low speed. The control surfaces are deflected and reconfigured to their predetermined optimal positions when the aircraft is in each of the aforementioned flight conditions. With respect to cruise, the reconfiguration control system will maximize the lift to drag ratio and keep the aircraft trimmed at a stable angle of attack. In a pitch maneuver, the control surfaces are deflected to pitch the aircraft and increase lift. Moreover, this increased lift has its spanwise center of pressure shifted inboard relative to its location for cruise. This inboard shifting reduces the increased bending moment about the aircraft's x-axis occasioned by the increased pitch force acting normal to the wing. To optimize high lift at low speed, during take-off and landing for example, the control surfaces are reconfigured to increase the local maximum coefficient of lift at stall-critical spanwise locations while providing pitch trim with control surfaces that are not stall critical.

摘要翻译： 独立可偏转的控制表面位于混合翼体飞机的翼的后缘。 本发明的重新配置控制系统控制每个控制表面的偏转，以优化在几个飞行条件（例如巡航，俯仰机动和低速下的高升程）中的每一个的机翼上的跨度升力分布。 当飞行器处于上述每个飞行条件时，控制表面被偏转并重新配置到其预定的最佳位置。 关于巡航，重新配置控制系统将使升力与牵引比达到最大，并保持飞行器处于稳定的迎角。 在俯仰操纵中，控制面被偏转以使飞机俯仰并增加升力。 此外，这种增加的升力，其翼展中心的压力相对于其巡航位置在内侧移动。 这种内侧换档减少了由垂直于机翼作用的俯仰力增加而引起的飞机X轴的弯矩增加。 为了优化低速提升，例如在起飞和着陆期间，控制表面被重新配置，以增加在失速临界翼展方向位置处的局部最大升力系数，同时为没有停止关键的控制面提供桨距修剪。

公开(公告)号：US20020063187A1

公开(公告)日：2002-05-30

申请号：US09983469

申请日：2001-10-24

发明人： Alain Depeige ,  Jean-Luc Jarrige

IPC分类号： B64D001/08 ,  B64C001/22 ,  B64D009/00

CPC分类号： B64D25/14 ,  B64C39/02 ,  B64C39/10 ,  B64C2039/105

摘要： The boarding device consists of at least one tunnel (20) connected to the outside of the aerodynamic shell (12) of the aircraft. More precisely, the tunnel is attached to the trailing edge of the fairing (12) and it extends aft approximately parallel to the longitudinal axis of the aircraft. A door (22) closes off the opening between the passenger cabin (10) and the tunnel (20). The rear part (26) of the tunnel (20) is articulated and/or detachable. In order to evacuate the passengers in an emergency, the front, fixed part of the tunnel (24) can be fitted with an inflatable escape slide or an articulated floor.

摘要翻译： 该登机装置包括至少一个连接到飞行器的空气动力学外壳（12）的外部的隧道（20）。 更准确地说，隧道连接到整流罩（12）的后缘，并且其大致平行于飞行器的纵向轴线延伸。 门（22）关闭客舱（10）和隧道（20）之间的开口。 隧道（20）的后部（26）铰接和/或可拆卸。 为了在紧急情况下撤离乘客，隧道（24）的前部，固定部分可以装有可充气逃生滑道或铰接地板。

公开(公告)号：US20020005454A1

公开(公告)日：2002-01-17

申请号：US09826424

申请日：2001-04-03

发明人： Paul B. MacCready ,  Bart D. .Hibbs ,  Robert F. Curtin ,  Kyle D. Swanson ,  Paul Belik

IPC分类号： B64C001/00 ,  B64B001/20 ,  B64C017/00

CPC分类号： B64D27/24 ,  B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187 ,  B64D27/02 ,  B64D37/30 ,  B64D2041/005 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44 ,  Y02T50/64 ,  Y02T90/36

摘要： Disclosed is an aircraft, configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The aircraft includes an extendable slat at the leading edge of the wing, and a reflexed trailing edge. The aircraft comprises a flying wing extending laterally between two ends and a center point. The wing is swept and has a relatively constant chord. The aircraft also includes a power module configured to provide power via a fuel cell. The fuel cell stores liquid hydrogen as fuel, but uses gaseous hydrogen in the fuel cell. A fuel tank heater is used to control the boil-rate of the fuel in the fuel tank. The aircraft of the invention includes a support structure including a plurality of supports, where the supports form a tetrahedron that affixes to the wing.

摘要翻译： 公开了一种被配置为具有宽范围的飞行速度的飞机，在延长的时间段内消耗低水平的功率，同时以无阻碍的向下观看的方式支持通信平台。 飞机在翼的前缘包括可延伸的板条，以及反射的后缘。 飞机包括在两端之间横向延伸的飞翼和中心点。 机翼被扫掠并具有相对恒定的和弦。 该飞机还包括被配置为经由燃料电池提供电力的功率模块。 燃料电池将液态氢作为燃料储存，而在燃料电池中使用气态氢。 燃料箱加热器用于控制燃料箱中的燃料的沸腾率。 本发明的飞行器包括支撑结构，该支撑结构包括多个支撑件，其中支撑件形成固定在机翼上的四面体。

公开(公告)号：US6102332A

公开(公告)日：2000-08-15

申请号：US086093

申请日：1998-05-28

申请人： Phil Haxton ,  Thomas W. Carlyle

发明人： Phil Haxton ,  Thomas W. Carlyle

IPC分类号： B64C39/02 ,  B64C39/10 ,  B64D25/12 ,  B64D27/02 ,  B64D9/00

CPC分类号： B64C39/02 ,  B64C39/10 ,  B64D25/12 ,  B64D27/02 ,  Y02T50/44

摘要： A method of transporting large numbers of passengers by air from a departure airfield to a destination airfield. The method comprises providing a large flying wing airframe, providing a plurality of passenger pods adapted to be loaded with passengers at a traditional airport gate facility, loading the pods with passengers, transporting the loaded pods to the airframe parked on the tarmac, attaching the loaded pods to the underside of the airframe, and flying the airframe to the destination airfield. The method further comprises detaching the pods from the airframe in the event of an in-flight emergency and deploying parachutes from the detached pods to lower them safely to the ground. A high density air transport system that embodies the method of the invention is also provided.

摘要翻译： 将大量乘客从出发机场运送到目的地机场的方法。 该方法包括提供大型飞翼机身，提供多个乘客舱，其适于在传统机场闸门设施处装载乘客，将货舱装载乘客，将装载的货舱运送到停放在停机坪上的机身上， 荚到机身的下侧，并将机身飞到目的地机场。 该方法还包括在飞行中紧急情况下将舱架从机体分离出来，并且从分离的舱部署部署降落伞以将它们安全地降落到地面。 还提供了体现本发明方法的高密度空气输送系统。

公开(公告)号：US5909858A

公开(公告)日：1999-06-08

申请号：US878623

申请日：1997-06-19

申请人： Arthur V. Hawley

发明人： Arthur V. Hawley

IPC分类号： B64C3/00 ,  B64C39/10

CPC分类号： B64C3/00 ,  B64C39/10 ,  B64C2039/105

摘要： A blended wing-body aircraft includes a central body, a wing, and a transition section which interconnects the body and the wing on each side of the aircraft. The two transition sections are identical, and each has a variable chord length and thickness which varies in proportion to the chord length. This enables the transition section to connect the thin wing to the thicker body. Each transition section has a negative sweep angle.

摘要翻译： 混合翼体飞机包括中心体，机翼和过渡部分，其将身体和飞机两侧的机翼相互连接。 两个过渡部分是相同的，并且每个过渡部分具有与弦长成比例变化的可变弦长和厚度。 这使得过渡部分能够将薄翼连接到较厚的主体。 每个过渡段具有负的扫掠角度。

公开(公告)号：US5810284A

公开(公告)日：1998-09-22

申请号：US404540

申请日：1995-03-15

申请人： Bart D. Hibbs ,  Peter B. S. Lissaman ,  Walter R. Morgan ,  Robert L. Radkey

发明人： Bart D. Hibbs ,  Peter B. S. Lissaman ,  Walter R. Morgan ,  Robert L. Radkey

IPC分类号： B64C39/10 ,  H04B7/185

CPC分类号： B64D27/24 ,  B64C39/10 ,  H04B7/18504 ,  B64D2211/00 ,  Y02T50/12 ,  Y02T50/44 ,  Y02T50/62 ,  Y02T50/69

摘要： This disclosure provides a solar rechargeable aircraft that is inexpensive to produce, is steerable, and can remain airborne almost indefinitely. The preferred aircraft is a span-loaded flying wing, having no fuselage or rudder. Travelling at relatively slow speeds, and having a two-hundred foot wingspan that mounts photovoltaic cells on most all of the wing's top surface, the aircraft uses only differential thrust of its eight propellers to turn. Each of five sections of the wing has one or more engines and photovoltaic arrays, and produces its own lift independent of the other sections, to avoid loading them. Five two-sided photovoltaic arrays, in all, are mounted on the wing, and receive photovoltaic energy both incident on top of the wing, and which is incident also from below, through a bottom, transparent surface. The aircraft is capable of a top speed of about ninety miles per hour, which enables the aircraft to attain and can continuously maintain altitudes of up to sixty-five thousand feet. Regenerative fuel cells in the wing store excess electricity for use at night, such that the aircraft can sustain its elevation indefinitely. A main spar of the wing doubles as a pressure vessel that houses hydrogen and oxygen gasses for use in the regenerative fuel cell. The aircraft has a wide variety of applications, which include weather monitoring and atmospheric testing, communications, surveillance, and other applications as well.

摘要翻译： 本公开提供了一种太阳能可再充电飞机，其生产便宜，是可操纵的，并且几乎可以无限期地保持空中飞行。 首选飞机是一个装有跨距的飞翼，没有机身或方向舵。 以相对较慢的速度行驶，并且拥有两百英尺的翼展，将光伏电池安装在大部分机翼的顶部表面上，飞机只使用其八个螺旋桨的差动推力来转动。 翼的五个部分中的每一个具有一个或多个发动机和光伏阵列，并且独立于其他部分产生其自己的升降机，以避免加载它们。 五个双面光伏阵列总体上安装在机翼上，并且接收能量入射到机翼的顶部并且从下方入射的光能通过底部的透明表面。 该飞机的最高时速约为每小时九十英里，这使飞机能够获得并可以持续维持高达六万五千英尺的高度。 机翼中的再生燃料电池储存了夜间使用的过量电力，使飞机能够无限期地维持其高度。 翼的主要翼梁加倍，作为容纳用于再生燃料电池的氢气和氧气的压力容器。 该飞机有各种各样的应用，包括天气监测和大气测试，通信，监视和其他应用程序。

公开(公告)号：US5090636A

公开(公告)日：1992-02-25

申请号：US644832

申请日：1991-01-23

申请人： James M. Sadowski

发明人： James M. Sadowski

IPC分类号： A63H27/00 ,  B64C39/10

CPC分类号： A63H27/00 ,  B64C39/10

摘要： An aircraft comprises a body portion and a pair of wings extending from either side of the body portion. An upward step is formed in the underside of the body portion in the center of the aircraft, and defines a rearwardly facing riser surface. The riser surface extends outwardly toward the wing tips, terminating substantially inwardly of the wing tips so that a majority of the length of the underside of each wing is uninterrupted by the riser surface. The step is located at the front-to-rear center of gravity of the aircraft, and provides an area of low pressure adjacent the riser surface to maintain the rear portion of the aircraft down. The aircraft can be constructed either as a full-scale or a small-scale aircraft.

摘要翻译： 飞行器包括主体部分和从主体部分的任一侧延伸的一对翼部。 在飞行器中心的主体部分的下侧形成向上的台阶，并且限定了向后的提升板表面。 提升管表面朝向翼尖向外延伸，终止于翼尖的基本上向内，使得每个翼的下侧的大部分长度不被提升管表面中断。 该步骤位于飞机的前后重心处，并且在提升管表面附近提供低压区域以保持飞机的后部部分下降。 该飞机可以作为全尺寸或小型飞机构建。