公开(公告)号：US20070246601A1

公开(公告)日：2007-10-25

申请号：US11245580

申请日：2005-10-07

Applicant: Otis Layton

Inventor： Otis Layton

IPC: B64C29/00

CPC classification number: B64C39/024 ,  B64C29/0025 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/167 ,  Y02T50/12

Abstract: A manned/unmanned, autotonomously or remotely directed, horizontal, or vertical take-off and landing (HOVTOL) aircraft. This air vehicle incorporates multiple vertical facing ducted fans (shrouded propellers) driven by at least one power plant. Control authority of said air vehicle when in vertical flight mode is maintained through varying and vectoring the thrust produced by said ducted fans. When in a conventional horizontal flight mode, the aircraft would rely on aerodynamic control surfaces. In one embodiment this air vehicle would have the ability to transition from vertical helicopter type flight to a conventional horizontal aircraft mode of flight and back again. In another embodiment, this aircraft would perform similar to a helicopter—using only its ducted fans to produce vertical lift and maneuver in three dimensions.

Abstract translation: 载人/无人驾驶，自动或遥控，水平或垂直起飞和着陆（HOVTOL）飞机。 这种空中车辆包含由至少一个发电厂驱动的多个垂直面对的管道风扇（被覆盖的螺旋桨）。 在垂直飞行模式下，所述空中客车的控制权限是通过改变和对向由所述管道风扇产生的推力来维持的。 在常规水平飞行模式下，飞机将依靠空气动力学控制面。 在一个实施例中，该空中飞行器将具有从垂直直升机类型飞行转换到常规水平飞行器飞行模式并再次返回的能力。 在另一个实施例中，该飞机将执行类似于直升机，仅使用其管道风扇来产生三维垂直升降和机动。

公开(公告)号：US07198225B2

公开(公告)日：2007-04-03

申请号：US10310415

申请日：2002-12-05

Applicant: Derek L. Lisoski ,  Greg T. Kendall

Inventor： Derek L. Lisoski ,  Greg T. Kendall

IPC: B64D27/00

CPC classification number: B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64D27/24 ,  B64D31/06 ,  B64D2211/00 ,  G05D1/0022 ,  G05D1/0077 ,  H04B7/18504 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/44 ,  Y02T50/55 ,  Y02T50/62

Abstract: A solar rechargeable, long-duration, span-loaded flying wing, having no fuselage or rudder. 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, pitch and yaw. The wing is configured to deform under flight loads to position the propellers such that the control can be achieved. Each of five segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other segments, 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.

Abstract translation: 太阳能可再充电，长时间，跨度的飞翼，没有机身或方向舵。 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速推力来转弯，俯仰和偏航。 机翼构造成在飞行载荷下变形以定位螺旋桨，使得可以实现控制。 翼的五个部分中的每一个具有一个或多个电动机和光伏阵列，并且独立于其它部分产生其自身的升降机，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。

公开(公告)号：US06793171B1

公开(公告)日：2004-09-21

申请号：US10406047

申请日：2003-04-02

Applicant: Walter D. Clark

Inventor： Walter D. Clark

IPC: B64D1100

CPC classification number: B64C39/024 ,  B64C17/00 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/22

Abstract: A method for flying an aircraft includes flying the aircraft at a first approximately level position and changing the flight of the aircraft from the first approximately level position to a climbing position. The method includes changing the flight of the aircraft from the climbing position to a second approximately level position to achieve a weightless state during the change to the second approximately level position and rolling the aircraft during the weightless state using one or more rolling control surfaces of the aircraft to establish a bank for a turn without creating adverse yaw. The aircraft does not include a deflectable spoiler, fin or rudder to counter adverse yaw. The rolling control surfaces of the aircraft may comprise elevons of the aircraft.

Abstract translation: 用于飞行飞行器的方法包括以第一近似水平位置飞行飞行器，并且将飞行器的飞行从第一近似水平位置改变到攀爬位置。 该方法包括将飞行器的飞行从爬升位置改变到第二近似水平位置，以在改变到第二近似水平位置期间实现失重状态，并且在失重状态期间使用一个或多个滚动控制表面滚动飞行器 飞机建立一个转弯的银行，而不会造成不利的偏航。 飞机不包括可偏转的扰流板，翅片或方向舵以抵御不利的偏航。 飞行器的滚动控制表面可以包括飞机的升降机。

公开(公告)号：US20040118969A1

公开(公告)日：2004-06-24

申请号：US10600258

申请日：2003-06-20

Inventor： Paul B. MacCready ,  Bart D. Hibbs ,  Kyle D. Swanson ,  Robert F. Curtin

IPC: B64B001/20 ,  B64C017/00

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

Abstract: 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 fuel cell compresses ambient air for an oxidizer, and operates with the fuel and oxidizer at pressures below one atmosphere. 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.

Abstract translation: 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。 燃料电池压缩氧化剂的环境空气，并在低于一个大气压的燃料和氧化剂下操作。 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：US20030192985A1

公开(公告)日：2003-10-16

申请号：US10408981

申请日：2003-04-08

Inventor： Jay Lipeles

IPC: B64C001/00 ,  B64C003/00 ,  B64C005/00

CPC classification number: B64C39/024 ,  B64C3/30 ,  B64C3/56 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/105 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/203 ,  B64C2201/22 ,  B64D33/04 ,  B64D2033/045

Abstract: The Duffel Bag Airplane is an inflatable flying wing unmanned airborne vehicle (UAV). The fuselage will house everything but the wings. The wing can be rolled up around the fuselage into a small package when deflated for easy transportation, such as by being carried in a duffle bag. Fabric construction, a small internal combustion engine with cooled exhaust, and wing warping controls combine to make the airplane inexpensive and extremely stealthy. All the usual signatures have been suppressed, which allow it to be used to make observations from close range under combat conditions. Control of this airplane is accomplished by warping the wings and is supplemented with stability augmentation.

Abstract translation: Duffel Bag飞机是一种充气飞翼无人机载机（UAV）。 机身将会容纳除翅膀之外的所有东西。 机翼可以卷绕在机身周围，当放气以便于运输时，例如通过携带在行李箱中，成为一个小包装。 织物结构，具有冷却排气的小型内燃机和机翼翘曲控制相结合，使飞机廉价而且非常隐蔽。 所有通常的签名已经被压制，这允许它用于在战斗条件下从近距离观察。 这架飞机的控制是通过扭转机翼来实现的，并补充了稳定性增强。

公开(公告)号：US06568635B2

公开(公告)日：2003-05-27

申请号：US09898631

申请日：2001-07-02

Applicant: Billy R. Carpenter

Inventor： Billy R. Carpenter

IPC: B64C2900

CPC classification number: B64C15/02 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/048 ,  B64C2201/22 ,  B64D27/02 ,  Y02T50/12 ,  Y02T50/44

Abstract: An apparatus and method for flight control of an aircraft provides a body with adjustable intake ports ducting air into an internal intake manifold. Adjusting the openings of the intake ports changes the amount of air flowing over the surfaces surrounding the intakes, changing the amount of lift created by those surfaces. The intake manifold feeds air to at least one engine, and an exhaust manifold communicates the exhaust of the engine to exhaust exit ports. The exhaust manifold contains a plurality of moveable components that direct exhaust within the exhaust manifold and to particular exhaust exit ports for producing various levels of force imbalance among the exit ports. A compressor powered by the engine provides air to bleed-air ports on the wings. Varying lift on the forward surfaces with the intake ports, vectored exhaust, and bleed air are used to control and stabilize the aircraft during flight, obviating the need for aerodynamic control surfaces.

Abstract translation: 用于飞机飞行控制的装置和方法为身体提供了将空气引导到内部进气歧管中的可调节进气口。 调整进气口的开口可改变在进气口周围的表面上流动的空气量，从而改变由这些表面产生的升力量。 进气歧管将空气供给至少一个发动机，并且排气歧管将发动机的排气与排气出口连通。 排气歧管包含多个可移动部件，其将排气歧管内的排气引导到特定排气出口，用于在出口之间产生不同程度的力不平衡。 由发动机供电的压缩机为机翼上的排气口提供空气。 使用进气口，向外排气和放气的前表面上的不同升力来控制和稳定飞行中的飞机，避免了空气动力学控制面的需要。

公开(公告)号：US06550717B2

公开(公告)日：2003-04-22

申请号：US09826424

申请日：2001-04-03

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

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

IPC: B64C100

CPC classification number: 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

Abstract: 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.

公开(公告)号：US20030001046A1

公开(公告)日：2003-01-02

申请号：US09898631

申请日：2001-07-02

Inventor： Billy R. Carpenter

IPC: B64C013/16

CPC classification number: B64C15/02 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/048 ,  B64C2201/22 ,  B64D27/02 ,  Y02T50/12 ,  Y02T50/44

Abstract: An apparatus and method for flight control of an aircraft provides a body with adjustable intake ports ducting air into an internal intake manifold. Adjusting the openings of the intake ports changes the amount of air flowing over the surfaces surrounding the intakes, changing the amount of lift created by those surfaces. The intake manifold feeds air to at least one engine, and an exhaust manifold communicates the exhaust of the engine to exhaust exit ports. The exhaust manifold contains a plurality of moveable components that direct exhaust within the exhaust manifold and to particular exhaust exit ports for producing various levels of force imbalance among the exit ports. A compressor powered by the engine provides air to bleed-air ports on the wings. Varying lift on the forward surfaces with the intake ports, vectored exhaust, and bleed air are used to control and stabilize the aircraft during flight, obviating the need for aerodynamic control surfaces

Abstract translation: 用于飞机飞行控制的装置和方法为身体提供了将空气引导到内部进气歧管中的可调节进气口。 调整进气口的开口可改变在进气口周围的表面上流动的空气量，从而改变由这些表面产生的升力量。 进气歧管将空气供给至少一个发动机，并且排气歧管将发动机的排气与排气出口连通。 排气歧管包含多个可移动部件，其将排气歧管内的排气引导到特定排气出口，用于在出口之间产生不同程度的力不平衡。 由发动机供电的压缩机为机翼上的排气口提供空气。 前进表面上带有进气口，向导排气和排气的不同升降机用于在飞行过程中控制和稳定飞机，避免了空气动力学控制面的需要

公开(公告)号：US20030001045A1

公开(公告)日：2003-01-02

申请号：US09895332

申请日：2001-07-02

Applicant: ELSE Ltd.

Inventor： Aharon Yifrach

IPC: B64C003/00

CPC classification number: B64C39/024 ,  B64C3/56 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/167 ,  B64C2201/201 ,  B64D5/00 ,  Y10S244/90 ,  Y10S244/901

Abstract: An unmanned flying vehicle comprises an autonomous flying wing having at least two wing portions arranged substantially symmetrically about a center portion. Each wing portion is pivotally attached to each adjoining portion such that the wing portions are foldable for storage and openable for deployment. A preferred form is the so-called seagull wing having four wing portions. The vehicles may be programmable from a mother aircraft whilst being borne to a deployment zone using a data link which may be wireless.