公开(公告)号：WO2013060318A1

公开(公告)日：2013-05-02

申请号：PCT/DE2012/001021

申请日：2012-10-20

Applicant: EADS DEUTSCHLAND GMBH

Inventor： HIEBL, Manfred ,  PONGRATZ, Hans Wolfgang

IPC: B64C3/30 ,  B64C39/02

CPC classification number: B64C39/02 ,  B64C3/30 ,  B64C9/00 ,  B64C27/41 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/105 ,  B64C2201/122 ,  B64C2201/165 ,  B64D39/00 ,  B64D2041/005 ,  B64D2211/00 ,  Y02T90/36

Abstract: Ein unbemanntes Höhenluftfahrzeug, insbesondere Stratosphären-Luftfahrzeug, mit zumindest einem Rumpf (10), Tragflügeln (13, 14), Steuerflächen (13", 14", 20', 20", 21 ', 21") und zumindest einer Antriebseinrichtung (15, 16, 17), die zumindest eine Antriebsmaschine und zumindest einen Propeller (15', 16', 17') aufweist, zeichnet sich dadurch aus, dass der jeweilige Tragflügel (13, 14) eine Mehrzahl von sich in einer Richtung quer, vorzugsweise rechtwinklig, zur Rumpflängsachse (Z) erstreckenden Flügelholmen (46', 46") und Schläuchen (40, 41, 42, 43, 44) aufweist, die von einer eine Flügelbespannung (45) bildenden Haut umgeben sind, welche die Querschnittskontur des Tragflügels bestimmt, wobei die Querschnittskontur ein Laminarprofil bildet, das bei geringem Strömungswiderstand einen hohen Auftrieb erzeugt; dass der jeweilige Tragflügel (13, 14) an seinem vom Rumpf (10) abgewandten freien Ende mit einem sich quer zur Tragflügellängsachse erstreckenden Winglet (13', 14') versehen ist und dass das Winglet (13', 14') mit einer bewegbaren Steuerfläche (13", 14") versehen ist, die die Erzeugung einer aerodynamischen Seitenkraft ermöglicht, um das Luftfahrzeug in eine Schrägrolllage zu bringen.

Abstract translation: 无人驾驶高空的飞机，特别是平流层飞行器，具有至少一个主体（10），翼片（13，14），凸轮表面（13”，14" ，20”，20”，21' ，21" ）和至少一个驱动装置（15 ，16，其具有至少一个驱动机和至少一个推进器（15“ 16' ，17”）17），其特征在于，相应的翼（13，14）具有多个横向的本身在一个方向上，优选 直角，以延伸护翼构件机身纵向轴线（Z）（46”，46“）和管（40，41，42，43，44），一个翼覆盖的形成（45）皮肤包围，这决定了机翼的横截面轮廓 其中，所述横截面轮廓形成了一个层流分布，这产生在低流动阻力的高扬程，即面向远离机身各翼（13，14）（10）的自由端具有横向延伸到翼型件纵向轴线的小翼（13”，14' ）已经 rsehen并且所述小翼（13”，14' ）上设置有可移动的控制表面（13”，14" ），这使得空气动力学侧力的产生，使飞机在倾斜辊的位置。

公开(公告)号：EP3013686B1

公开(公告)日：2017-04-05

申请号：EP14752660.2

申请日：2014-06-30

Applicant: Bellezza Quater, Paolo

Inventor： Bellezza Quater, Paolo

IPC: B64C27/20 ,  B64B1/34 ,  B64C3/30 ,  B64C39/02 ,  B64B1/30

CPC classification number: B64C39/024 ,  B64B1/34 ,  B64C3/30 ,  B64C27/20 ,  B64C2201/022 ,  B64C2201/027 ,  B64C2201/101 ,  B64C2201/105 ,  B64C2201/165

公开(公告)号：EP2773556A1

公开(公告)日：2014-09-10

申请号：EP12805568.8

申请日：2012-10-20

Applicant: EADS Deutschland GmbH

Inventor： HIEBL, Manfred ,  PONGRATZ, Hans Wolfgang

IPC: B64C3/30 ,  B64C39/02

CPC classification number: B64C39/02 ,  B64C3/30 ,  B64C9/00 ,  B64C27/41 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/105 ,  B64C2201/122 ,  B64C2201/165 ,  B64D39/00 ,  B64D2041/005 ,  B64D2211/00 ,  Y02T90/36

Abstract: An unmanned high altitude aircraft, in particular a stratosphere aircraft, comprising at least one fuselage (10), wings (13, 14), control surfaces (13", 14", 20', 20", 21', 21") and at least one drive device (15, 16, 17) that has at least one drive machine and at least one propeller (15', 16' 17'), is characterised in that each wing (13, 14) has a plurality of tubes (40, 41, 42, 43, 44) and wing spars (46' 46") that extend in one direction transversally, preferably perpendicularly, to the longitudinal axis of the fuselage (Z) and are surrounded by a skin that forms a wing covering (45) and defines the cross-sectional contour of the wing, the cross-sectional contour forming a laminar profile that generates high lift when there is low flow resistance. Each wing (13, 14) is provided with a winglet (13', 14') that extends transversally to the longitudinal axis of the wing on its free end which faces away from the fuselage (10), and the winglet (13' 14') is provided with a movable control surface (13", 14") that enables an aerodynamic side force to be generated in order to bring the aircraft into an oblique bank position.

Abstract translation: 高空无人空中平流层飞行器包括机身，机翼，控制面和包括发动机和螺旋桨的推进系统。 每个翼具有沿垂直于纵向机身轴线的方向延伸的多个软管和翼梁，并且被形成机翼覆盖物的皮肤包围，所述机翼覆盖物确定机翼的横截面轮廓，横截面轮廓形成层流 当流动阻力低时产生高升力的翼型。 在远离机身的自由端处，每个机翼具有横向于纵向翼轴线延伸的小翼。 小翼具有可移动的控制表面，其允许产生空气动力学侧力，以使空中飞行器处于堆积位置。

公开(公告)号：EP2521670A1

公开(公告)日：2012-11-14

申请号：EP09760232.0

申请日：2009-10-28

Applicant: Swissavia

Inventor： BERTHIER, Bernard

IPC: B64C31/036 ,  B64C39/02

CPC classification number: B64C31/036 ,  B64C39/024 ,  B64C2201/105 ,  B64C2201/107

Abstract: The invention relates to an automatic takeoff method for an aircraft with a flexible airfoil, comprising a carriage suspended by rigging lines from an airfoil. According to said method: - said carriage is provided with an autopilot controlling actuators that control said rigging lines; - said airfoil is provided with an airfoil attitude sensor, comprising a biaxial accelerometer and a biaxial rate gyro, capable of defining the position of an airfoil reference frame in relation to the ground, and means for communicating with said autopilot; - during takeoff, information is received from said airfoil attitude sensor and transmitted to said autopilot for the purpose of controlling said actuators. The invention also relates to an airfoil for the implementation of said method, comprising an airfoil attitude sensor with an inertial unit with a biaxial accelerometer and a biaxial rate gyro, and means for communicating with an autopilot. The invention further relates to an aircraft comprising such an airfoil.

公开(公告)号：EP1289830A2

公开(公告)日：2003-03-12

申请号：EP01944161.7

申请日：2001-05-23

Applicant: LIOTTA, Lance A.

Inventor： LIOTTA, Lance A.

IPC: B64C3/00

CPC classification number: B64C39/066 ,  A63H27/00 ,  B64C39/028 ,  B64C2201/105 ,  B64C2201/107

Abstract: An aircraft which is designed for remote controlled slow flight, indoor or in a small outdoor yard or field. The aerial lifting body is defined by a series of lightweight planar or thin airfoil surfaces (A1, A2, A3, A4) arranged in a radially symmetrical configuration. Suspended within the cavity (O) formed by the thin airfoil surfaces (A1, A2, A3, A4) is a thrust generating propeller system (C) that is angled upwardly and that can be regulated remotely so as to change the angle of the thrust vector within the cavity (O) for steering. Lifting, stability, turning, and general control of the direction of motion in flight is accomplished without any formal wings, rudder, tail, or control surfaces.

公开(公告)号：US20140255189A1

公开(公告)日：2014-09-11

申请号：US14250385

申请日：2014-04-11

Applicant: The Boeing Company

Inventor： Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

IPC: B64C3/30

CPC classification number: B64C3/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/105

Abstract: A method and apparatus for operating an airfoil system. A gas may be generated. The gas may be sent into an inflatable airfoil system comprising an inflatable air foil and a section. The inflatable airfoil may have an inner end and an outer end in which the inflatable airfoil may be comprised of a number of materials that substantially pass electromagnetic waves through the inflatable airfoil. The section may have a number of openings in which the inner end of the inflatable airfoil may be associated with the section. The section may be configured to be associated with a fuselage. The number of openings may be configured to provide communications with an interior of the inflatable airfoil. The section with the number of openings may be configured to reduce reflection of the electromagnetic waves encountering the section.

Abstract translation: 一种用于操作翼型系统的方法和装置。 可能产生气体。 气体可以被送入包括可膨胀的气翼和截面的充气翼型系统中。 可膨胀翼型件可以具有内端和外端，其中可膨胀翼型可以由许多基本上通过电磁波通过可充气翼型的材料构成。 该部分可以具有多个开口，其中可充气翼片的内端可以与该部分相关联。 该部分可以被配置为与机身相关联。 开口的数量可以被配置为提供与可膨胀翼型件的内部的通信。 具有开口数量的部分可以被配置为减少遇到该部分的电磁波的反射。

公开(公告)号：US20120211598A1

公开(公告)日：2012-08-23

申请号：US13445708

申请日：2012-04-12

Applicant: Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

Inventor： Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

IPC: B64C13/00 ,  B64C13/28 ,  B64C3/46

CPC classification number: B64C1/34 ,  B64C3/385 ,  B64C13/28 ,  B64C2201/105 ,  Y02T50/14

Abstract: An apparatus may comprise an inflatable control surface for an aircraft and an end of the inflatable control surface configured for attachment to a fuselage of the aircraft. The end of the inflatable control surface may be configured to be rotated about an axis to control movement of the aircraft during flight.

Abstract translation: 装置可以包括用于飞行器的可充气控制表面和构造成附接到飞行器的机身的可充气控制表面的一端。 可充气控制表面的端部可以被构造为绕轴线旋转以控制飞行器在飞行过程中的运动。

公开(公告)号：US20120109427A1

公开(公告)日：2012-05-03

申请号：US13381197

申请日：2009-10-28

Applicant: Bernard Berthier

Inventor： Bernard Berthier

IPC: G05D1/00 ,  B64C31/036

CPC classification number: B64C31/036 ,  B64C39/024 ,  B64C2201/105 ,  B64C2201/107

Abstract: The invention relates to an automatic takeoff method for an aircraft with a flexible airfoil, comprising a carriage suspended by rigging lines from an airfoil. According to said method:—said carriage is provided with an autopilot controlling actuators that control said rigging lines;—said airfoil is provided with an airfoil attitude sensor, comprising a biaxial accelerometer and a biaxial rate gyro, capable of defining the position of an airfoil reference frame in relation to the ground, and means for communicating with said autopilot;—during takeoff, information is received from said airfoil attitude sensor and transmitted to said autopilot for the purpose of controlling said actuators. The invention also relates to an airfoil for the implementation of said method, comprising an airfoil attitude sensor with an inertial unit with a biaxial accelerometer and a biaxial rate gyro, and means for communicating with an autopilot. The invention further relates to an aircraft comprising such an airfoil.

Abstract translation: 本发明涉及一种具有柔性翼型的飞行器的自动起飞方法，该飞行器包括通过从翼型装配线路悬挂的滑架。 根据所述方法：托架提供有控制所述索具线的自动驾驶控制致动器;所述翼型件设置有翼型姿态传感器，包括双轴加速度计和双轴率陀螺仪，能够限定翼型的位置 相对于地面的参考框架和用于与所述自动驾驶仪通信的装置; - 在起飞时，从所述翼型姿态传感器接收信息并传送到所述自动驾驶仪，以控制所述致动器。 本发明还涉及一种用于实现所述方法的翼型件，包括具有带有双轴加速度计和双轴率陀螺仪的​​惯性单元的翼型姿态传感器和用于与自动驾驶仪通信的装置。 本发明还涉及一种包括这种翼型的飞行器。

公开(公告)号：US20110127373A1

公开(公告)日：2011-06-02

申请号：US11217851

申请日：2005-09-01

Applicant: James P. Thomas ,  Jared N. Baucom ,  William R. Pogue, III ,  Muhammad A. Qidwai

Inventor： James P. Thomas ,  Jared N. Baucom ,  William R. Pogue, III ,  Muhammad A. Qidwai

IPC: B64C11/00 ,  H01L35/30 ,  F16L3/01

CPC classification number: B64C1/34 ,  B64C3/185 ,  B64C3/34 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/105 ,  B64D27/24 ,  B64D37/04 ,  B64D37/06 ,  B64D37/30 ,  B64D41/00 ,  H01L35/30 ,  Y02T50/44 ,  Y02T50/53 ,  Y02T50/62

Abstract: A vehicle including at least one bladder for containing a fuel as liquid and gas at a predetermined pressure, with a bladder outlet arranged to releasing fuel from the bladder and to maintain the fuel in the bladder at the predetermined pressure, the fuel provides thrust to the vehicle upon combustion, the fuel-filled bladder providing initial structural integrity of the vehicle. In an exemplary embodiment, the vehicle is an unmanned anal vehicle. A combustion chamber and thermoelectric conversion module can generate electricity for a propellor and battery from the fuel supply. Internal vapor pressure is maintained until the fuel bladder is empty.

Abstract translation: 一种车辆，包括用于将燃料作为液体和气体以预定压力容纳的至少一个气囊，其中气囊出口布置成从气囊释放燃料并将气体中的燃料保持在预定压力，燃料提供推力 燃料填充的气囊提供车辆的初始结构完整性。 在示例性实施例中，车辆是无人驾驶的肛门车辆。 燃烧室和热电转换模块可以从燃料供应器为推进器和电池发电。 保持内部蒸汽压力，直到燃料囊为空。

公开(公告)号：US20090045284A1

公开(公告)日：2009-02-19

申请号：US11840607

申请日：2007-08-17

Applicant: Adam N. Chu

Inventor： Adam N. Chu

IPC: B64B1/00

CPC classification number: B64C39/024 ,  B64B1/02 ,  B64C2201/022 ,  B64C2201/101 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/165

Abstract: An orientation system is disclosed for a lighter-than-air aircraft having a lower stage suspended from an envelope. The orientation system includes cords interconnecting the envelope and the lower stage and means for adjusting the length of at least one of the cords between the lower stage and the envelope. Adjusting the length produces a shift in the angle of attack of the envelope with respect to the lower stage.

Abstract translation: 公开了一种具有从信封悬挂的较低级的轻型飞机的定向系统。 定向系统包括将信封和下层相互连接的绳索和用于调节下层和包封之间的至少一根帘线长度的装置。 调整长度会导致信封相对于下层的迎角发生偏移。