| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | 高空飞机、飞机单元以及用于运行飞机单元的方法 | CN201280052699.5 | 2012-10-20 | CN104053597A | 2014-09-17 | M.希布尔; H.蓬格拉茨 |
| 一种无人驾驶的高空飞机、尤其平流层飞机，其带有至少一个机身(10)、机翼(13，14)、控制面(13"，14"，20'，20"，21'，21")和具有至少一个驱动机器和至少一个螺旋桨(15'，16'，17')的至少一个驱动装置(15，16，17)，其特征在于，相应的机翼(13，14)具有在横向于、优选地垂直于机身纵轴线(Z)的方向上延伸的多个翼梁(46'，46")和软管(40，41，42，43，44)，其被形成翼罩(45)的表皮包围，该翼罩确定机翼的横截面轮廓，其中，该横截面轮廓形成层流翼型，其在较小的流动阻力下产生较高的升力；相应的机翼(13，14)在它的背离机身(10)的自由端部处设有横向于所述机翼纵轴线延伸的小翼(13'，14')，并且小翼(13'，14')设有可动的控制面(13"，14")，其使能够产生空气动力学侧向力，以将飞机带到倾斜转动位置中。 | ||||||
| 2 | 带有柔性机翼的飞行器的自动起飞方法、帆和飞行器 | CN200980153185.7 | 2009-10-28 | CN102272003A | 2011-12-07 | B.贝尔捷 |
| 本发明涉及一种带有柔性机翼的飞行器的自动起飞的方法，其中所述飞行器包括由吊件悬挂在帆上的小车。根据该方法：为所述小车装备自动驾驶仪，该自动驾驶仪控制作用于所述吊件的致动器；为所述帆装备机翼高度传感器，该机翼高度传感器包括双轴加速度计和双轴陀螺测试仪，以及用于与所述自动驾驶仪通信的装置，其中所述陀螺测试仪能够确定帆参考系相对于地面的位置；当起飞时，收集来自于所述机翼高度传感器的信息，以将其传输给自动驾驶仪，以向所述致动器发出指令。本发明还涉及一种实施该方法的帆，其包括带有惯性仪的机翼高度传感器，该惯性仪带有双轴加速度计和双轴陀螺测试仪，以及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帆的飞行器。 | ||||||
| 3 | HYBRID LIGHTER-THAN-AIR VEHICLE | US14341184 | 2014-07-25 | US20160023748A1 | 2016-01-28 | Scott R. Kempshall |
| 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. | ||||||
| 4 | Variable pitch airfoils | US13445708 | 2012-04-12 | US08393576B2 | 2013-03-12 | Kevin Reed Lutke; Aaron Jonathan Kutzmann |
| 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. | ||||||
| 5 | Reinforced inflatable wings for fitment-constrained air vehicles | US12406173 | 2009-03-18 | US08104713B2 | 2012-01-31 | Terry M. Sanderson; Rudy A. Eisentraut; David B. Hatfield |
| 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 forms a first portion of the wing. A skin having a plurality of rigid plates 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. | ||||||
| 6 | Autophagous multifunction structure-power system | US11217851 | 2005-09-01 | US20110127373A1 | 2011-06-02 | James P. Thomas; Jared N. Baucom; William R. Pogue, III; Muhammad A. Qidwai |
| 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. | ||||||
| 7 | REINFORCED INFLATABLE WINGS FOR FITMENT-CONSTRAINED AIR VEHICLES | US12406173 | 2009-03-18 | US20100237192A1 | 2010-09-23 | Terry M. Sanderson; Rudy A. Eisentraut; David B. Hatfield |
| 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 forms a first portion of the wing. A skin having a plurality of rigid plates 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. | ||||||
| 8 | Deployment brake release for a parachute | US11645029 | 2006-12-26 | US07648105B2 | 2010-01-19 | Storm Dunker; Martin Gilbert |
| A deployment brake release system for use with an airborne guidance unit (AGU) of a parachute suitable for precision cargo delivery. The parachute includes deployment brake lines secured at one end to the edge of the canopy and connected at the other end through looped ends to motor control lines. The motor control lines are, in turn, engaged with the motor of the AGU. The deployment brake release system includes at least one hook mount having a hook secured to the AGU frame. The looped ends of the deployment brake lines are engaged with the hook during rigging so that, upon deployment, opening forces are applied to the hook mount rather than the motor. After full canopy inflation, the motor, via the motor control lines, pulls on the brake line looped ends to disengage them from the hook, transferring subsequent canopy loads to the AGU motor for the remainder of the flight. A method for releasing the deployment brake lines is also disclosed. | ||||||
| 9 | Deployment brake release for a parachute | US11645029 | 2006-12-26 | US20080149775A1 | 2008-06-26 | Storm Dunker; Martin Gilbert |
| A deployment brake release system for use with an airborne guidance unit (AGU) of a parachute suitable for precision cargo delivery. The parachute includes deployment brake lines secured at one end to the edge of the canopy and connected at the other end through looped ends to motor control lines. The motor control lines are, in turn, engaged with the motor of the AGU. The deployment brake release system includes at least one hook mount having a hook secured to the AGU frame. The looped ends of the deployment brake lines are engaged with the hook during rigging so that, upon deployment, opening forces are applied to the hook mount rather than the motor. After full canopy inflation, the motor, via the motor control lines, pulls on the brake line looped ends to disengage them from the hook, transferring subsequent canopy loads to the AGU motor for the remainder of the flight. A method for releasing the deployment brake lines is also disclosed. | ||||||
| 10 | Inflatable aerodynamic wing and method | US10927579 | 2004-08-26 | US07185851B2 | 2007-03-06 | Daryl B. Elam |
| An inflatable structure constructed of flexible material that can occupy a minimal volume when in a deflated and stored condition as compared to its fully inflated and deployed configuration, has sufficient structural rigidity to function as a wing when deployed. The wing includes an array of inflatable chambers with generally circular cross-sections. The chambers are spaced a particular distance between their centers and held in that spacing by an outer wing skin. For equal cross-sectional diameter chambers this distance is less than the diameter. When the chambers are inflated the close spacing causes tension in the opposing surfaces to create a rigid structure. | ||||||
| 11 | Unmanned Urban Aerial Vehicle | US11307461 | 2006-02-08 | US20060284002A1 | 2006-12-21 | Kurt Stephens; David Burns |
| The proposed UUAV provides a small, agile vehicle that leverages the unique principals of remote controlled model aviation. The UUAV also encompasses an aerodynamically shaped, gas filled wing that can be used to provide buoyancy for lift assistance both through the use of the lighter than air gas and by its aerodynamic shape in forward flight. | ||||||
| 12 | Deployable, rigidizable wing | US10770130 | 2004-02-03 | US20050151007A1 | 2005-07-14 | David Cadogan; David Graziosi; Grant Lee; Stephen Scarborough; Timothy Smith |
| A novel design and construction method for an inflatable, rigidizable wing for a terrestrial or planetary flying vehicle. The wing is caused to deploy from an initially packed condition and to assume its functional shape by means of an inflation gas. After inflation, the wing is rigidized by any of several means, such that the inflation gas is no longer required. The composite wing is fabricated from a base reinforcement material, often a fabric, which is coated with a polymer resin that hardens when exposed to a curing mechanism. Several activation mechanisms exist by which to initiate rigidization of such a structure, including elevated temperature, ultraviolet light, and chemical constituents of the inflation gas. The resultant wing has fundamental advantages compared to existing inflatable wings, including improved stiffness, and reduced susceptibility to structural failure in response to puncture. | ||||||
| 13 | HÖHENLUFTFAHRZEUG, LUFTFAHRZEUGVERBAND UND VERFAHREN ZUM BETREIBEN EINES LUFTFAHRZEUGVERBANDS | EP12805568.8 | 2012-10-20 | EP2773556B1 | 2018-07-18 | HIEBL, Manfred; PONGRATZ, Hans Wolfgang |
| 14 | Adaptive solar airframe | EP14152285.4 | 2014-01-23 | EP2759469B1 | 2017-06-21 | Moussouris, John Peter; Frolov, Sergey V.; Cyrus, Michael |
| 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. | ||||||
| 15 | A MULTI-ROTOR AIRCRAFT | EP14752660.2 | 2014-06-30 | EP3013686A1 | 2016-05-04 | Bellezza Quater, Paolo |
| 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). | ||||||
| 16 | PROCEDE DE DECOLLAGE AUTOMATIQUE D'UN AERONEF A VOILURE SOUPLE, VOILE, ET AERONEF | EP09760232.0 | 2009-10-28 | EP2521670B1 | 2014-03-19 | BERTHIER, Bernard |
| 17 | A MULTI-ROTOR AIRCRAFT | EP14752660.2 | 2014-06-30 | EP3013686B1 | 2017-04-05 | Bellezza Quater, Paolo |
| 18 | REINFORCED INFLATABLE WINGS FOR FITMENT-CONSTRAINED AIR VEHICLES | EP10763896.7 | 2010-02-16 | EP2409113B1 | 2015-04-22 | SANDERSON, Terry, M.; EISENTRAUT, Rudy, A.; HATFIELD, David, B. |
| 19 | HÖHENLUFTFAHRZEUG, LUFTFAHRZEUGVERBAND UND VERFAHREN ZUM BETREIBEN EINES LUFTFAHRZEUGVERBANDS | EP12805568.8 | 2012-10-20 | EP2773556A1 | 2014-09-10 | HIEBL, Manfred; PONGRATZ, Hans Wolfgang |
| 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. | ||||||
| 20 | Adaptive solar airframe | EP14152285.4 | 2014-01-23 | EP2759469A1 | 2014-07-30 | Moussouris, John Peter; Frolov, Sergey V.; Cyrus, Michael |
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.
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