公开(公告)号：EP2759469B1

公开(公告)日：2017-06-21

申请号：EP14152285.4

申请日：2014-01-23

Applicant: Sunlight Photonics Inc.

Inventor： Moussouris, John Peter ,  Frolov, Sergey V. ,  Cyrus, Michael

IPC: B64C1/34 ,  B64C3/46 ,  B64C39/02 ,  B64D27/24 ,  G01S3/786

CPC classification number: B64C1/0009 ,  B64C1/34 ,  B64C3/46 ,  B64C39/024 ,  B64C2201/105 ,  B64D2211/00 ,  G01S3/7861 ,  Y02T50/14

Abstract: Methods and apparatus for an adaptable solar airframe are provided herein. In some embodiments, an adaptable solar airframe includes a solar PV system having at least one solar tracking system and being able to follow the sun position in order to increase sunlight collection and power output; and an expandable body having an aerodynamic cross-section that minimizes parasitic air drag at any given thickness of the body, further being at least partially transparent to sunlight, further enclosing the solar PV system, and further being able to change its shape in response to changes in the positions of the solar PV system.

Abstract translation: 本文提供了用于可适应的太阳能机身的方法和设备。 在一些实施例中，可适应的太阳能机身包括太阳能PV系统，其具有至少一个太阳能跟踪系统并且能够跟随太阳位置以增加太阳光收集和功率输出; 以及具有空气动力学横截面的可膨胀体，其使得在任何给定的身体厚度下的寄生空气阻力最小化，进一步对太阳光至少部分透明，进一步包围太阳能PV系统，并且还能够响应于 太阳能光伏系统位置的变化。

公开(公告)号：EP3013686A1

公开(公告)日：2016-05-04

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

Abstract: Described herein is a multi-rotor aircraft (10; 200) including: - a load-bearing structure (10A; 200A); and - a plurality of propulsion assemblies (M1, M2, M3, M4, M5, M6; M1', M2', M3', M4') each including a rotor (R1, R2, R3, R4, R5, R6; R1', R2', R3', R4'), which can be driven in rotation about a respective axis of rotation (X1, X2, X3, X4, X5, X6; X1', X2', X3', X4'), these propulsion assemblies being coupled to and supported by the load-bearing structure (10A; 200A), wherein the load-bearing structure (10A; 200A) is inflatable (C11, C12, C13, C14, C15, C16; C200).

Abstract translation: 这里描述的是多转子飞机（10; 200），包括： - 承重结构（10A; 200A）; 每个包括转子（R1，R2，R3，R4，R5，R6; R1）的推进组件（M1，M2，M3，M4，M5，M6; M1'，M2'，M3'，M4' （X1，X2，X3，X4，X5，X6; X1'，X2'，X3'，X4'）相对旋转驱动， 这些推进组件联接到承载结构（10A; 200A）并由其承载，其中承载结构（10A; 200A）是可膨胀的（C11，C12，C13，C14，C15，C16; C200）。

公开(公告)号：EP2409113B1

公开(公告)日：2015-04-22

申请号：EP10763896.7

申请日：2010-02-16

Applicant: Raytheon Company

Inventor： SANDERSON, Terry, M. ,  EISENTRAUT, Rudy, A. ,  HATFIELD, David, B.

IPC: F42B10/14 ,  F42B10/20

CPC classification number: B64C3/30 ,  B64C2201/102 ,  B64C2201/105 ,  F42B10/14 ,  F42B10/146 ,  F42B10/20

公开(公告)号：EP2409113A2

公开(公告)日：2012-01-25

申请号：EP10763896.7

申请日：2010-02-16

Applicant: Raytheon Company

Inventor： SANDERSON, Terry, M. ,  EISENTRAUT, Rudy, A. ,  HATFIELD, David, B.

IPC: F42B10/14 ,  F42B10/20

CPC classification number: B64C3/30 ,  B64C2201/102 ,  B64C2201/105 ,  F42B10/14 ,  F42B10/146 ,  F42B10/20

Abstract: A reinforced inflatable wing improves the tolerance of the OML and reinforces the wing in at least the high load areas. This approach provides fitment constrained air vehicles with wings having increased surface area to improve flight endurance or aerodynamic control. A wing box (20,108, 208, 308, 400) forms a first portion of the wing. A skin having a plurality of rigid plates (40,122, 222, 322, 406) affixed thereto is inflated to form a second portion of the wing to either increase the chord length or lengthen the wing span. The skin is suitably inflated with foam to form a solid wing.

公开(公告)号：EP1242279B1

公开(公告)日：2004-01-07

申请号：EP00990085.3

申请日：2000-12-20

Applicant: Institut de Recherche pour le Développement ( IRD)

Inventor： ASSELINE, Jean ,  DE NONI, George

IPC: B64C39/02 ,  B64C31/036 ,  B64D47/08

CPC classification number: A63H27/08 ,  A63H30/04 ,  B64C2201/086 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/187 ,  Y10S244/902 ,  Y10S244/903

Abstract: The invention concerns a small-size radio-controlled flying device propelled by a heat engine (20) with pusher propeller (10) for remote sensing, said device enabling short take-off and landing and a maximum flying speed of 34 Km/h. The device comprises a nacelle and a wing system, the nacelle (1) being a rigid three-wheeled carriage capable of being disassembled by denesting a more or less pyramidal jig with rear base (2) and front top (7), a lower plane (3) two lateral planes (4, 5) and an upper plane (6), the base being a single-piece welded element and comprising the engine, the propeller, a tank and the remote sensing unit, the top being a single-piece welded element, the lower plane and the two lateral planes comprising side members (11, 12) at least assembled at the base and at the top, the lower plane comprising at its three end angles two rear wheels (8) and a front wheel (9), the front wheel being arranged overlapping forward in the top and the wheels being low pressure tyres, the wing system (13) being a wing box flexible parafoil, said wing system being linked to the nacelle adjustable by two front suspension cables (17), two braking suspension cables (18) acting on the two flaps/wings.

公开(公告)号：EP1242279A1

公开(公告)日：2002-09-25

申请号：EP00990085.3

申请日：2000-12-20

Applicant: Institut de Recherche pour le Développement ( IRD)

Inventor： ASSELINE, Jean ,  DE NONI, George

IPC: B64C39/02 ,  B64C31/036 ,  B64D47/08

CPC classification number: A63H27/08 ,  A63H30/04 ,  B64C2201/086 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/187 ,  Y10S244/902 ,  Y10S244/903

Abstract: The invention concerns a small-size radio-controlled flying device propelled by a heat engine (20) with pusher propeller (10) for remote sensing, said device enabling short take-off and landing and a maximum flying speed of 34 Km/h. The device comprises a nacelle and a wing system, the nacelle (1) being a rigid three-wheeled carriage capable of being disassembled by denesting a more or less pyramidal jig with rear base (2) and front top (7), a lower plane (3) two lateral planes (4, 5) and an upper plane (6), the base being a single-piece welded element and comprising the engine, the propeller, a tank and the remote sensing unit, the top being a single-piece welded element, the lower plane and the two lateral planes comprising side members (11, 12) at least assembled at the base and at the top, the lower plane comprising at its three end angles two rear wheels (8) and a front wheel (9), the front wheel being arranged overlapping forward in the top and the wheels being low pressure tyres, the wing system (13) being a wing box flexible parafoil, said wing system being linked to the nacelle adjustable by two front suspension cables (17), two braking suspension cables (18) acting on the two flaps/wings.

公开(公告)号：US20180257760A1

公开(公告)日：2018-09-13

申请号：US15981623

申请日：2018-05-16

Applicant: The Boeing Company

Inventor： Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

IPC: B64C3/30 ,  B64C39/02

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.

公开(公告)号：US09975633B1

公开(公告)日：2018-05-22

申请号：US15151287

申请日：2016-05-10

Applicant: NORTHROP GRUMMAN SYSTEMS CORPORATION

Inventor： Stephen D. Johnson ,  Barnaby S. Wainfan

IPC: B64C39/02 ,  B64C3/00 ,  B64C7/02 ,  B64C11/00

CPC classification number: B64C39/024 ,  B64C3/00 ,  B64C7/02 ,  B64C11/001 ,  B64C2201/104 ,  B64C2201/105 ,  B64C2201/108 ,  B64C2201/162 ,  B64C2201/20

Abstract: A ducted fan UAV that can be collapsed into a stowed configuration and then deployed for flight by, for example, inflating the duct to a deployed configuration. The UAV includes a plurality of rotor blades, a plurality of struts and a plurality of control vanes each being pivotally mounted to a center body by a hinge so that the rotor blades, the struts and the control vanes can be folded into the stowed configuration to be substantially parallel to the center body and be unfolded into the deployed configuration to be substantially perpendicular to the center body. The UAV also includes a pressurization system providing a pressurant to a chamber within the duct so as to inflate the duct and cause the struts, the rotor blades and the control vanes to move from the stowed configuration to the deployed configuration.

公开(公告)号：US20160023748A1

公开(公告)日：2016-01-28

申请号：US14341184

申请日：2014-07-25

Applicant: Scott R. Kempshall

Inventor： Scott R. Kempshall

IPC: B64C3/44 ,  B64B1/58 ,  B64C3/54 ,  B64B1/08 ,  B64B1/14

CPC classification number: B64C3/46 ,  B64B1/08 ,  B64B1/14 ,  B64B1/26 ,  B64B1/58 ,  B64B2201/00 ,  B64C3/48 ,  B64C3/54 ,  B64C3/546 ,  B64C2201/022 ,  B64C2201/101 ,  B64C2201/105 ,  F03D1/04 ,  F03D9/25 ,  F03D9/32 ,  F05B2240/921 ,  Y02E10/725

Abstract: The present invention is a variable geometry lighter-than-air (LTA) aircraft that is adapted to morph its shape from a symmetric cross-section buoyant craft to an asymmetric lifting body and even to a symmetric zero lift configuration. The basic structure is a semi rigid airship with movable longerons. Movement of the longerons adjusts the camber of the upper and/or lower surfaces to achieve varying shapes of the lifting-body. This transformation changes both the lift and drag characteristics of the craft to alter the flight characteristics. The transformation may be accomplished while the craft is airborne and does not require any ground support equipment.

Abstract translation: 本发明是一种可变几何型轻型空中（LTA）飞机，其适于将其形状从对称横截面浮力工艺变形到非对称提升体，甚至变形成对称零升力构造。 基本结构是具有可移动隆起的半刚性飞艇。 仰角的运动调节上表面和/或下表面的弯度，以实现提升体的变化形状。 这种转变改变了飞行器的升力和阻力特性，以改变飞行特性。 转换可以在飞行器机载时完成，并且不需要任何地面支撑设备。

公开(公告)号：US20140252156A1

公开(公告)日：2014-09-11

申请号：US14354030

申请日：2012-10-20

Applicant: EADS Deutschland GmbH

Inventor： Manfred Hiebl ,  Hans Wolfgang Pongratz

IPC: B64C39/02 ,  B64D39/00 ,  B64C27/41 ,  B64C9/00

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 ,  Y02T50/55 ,  Y02T90/36

Abstract: A high-altitude unmanned stratosphere aerial vehicle includes a fuselage, wings, control surfaces, and a propulsion system including an engine and a propeller. Each wing has a plurality of hoses and wing spars extending in a direction perpendicularly to the longitudinal fuselage axis and are surrounded by a skin forming a wing covering that determines the cross-sectional contour of the wing, the cross-sectional contour forming a laminar flow airfoil that generates high lift when there is low flow resistance. At the free end facing away from the fuselage, each wing has a winglet extending transversely to the longitudinal wing axis. The winglet has a movable control surface, which allows an aerodynamic side force to be generated so as to bring the aerial vehicle to a banked position.

Abstract translation: 高空无人空中平流层飞行器包括机身，机翼，控制面，以及包括发动机和推进器的推进系统。 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。