公开(公告)号：US08727280B1

公开(公告)日：2014-05-20

申请号：US12633272

申请日：2009-12-08

Applicant: Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

Inventor： Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

IPC: B64C1/00 ,  B64C3/00 ,  B64C5/00

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：US08342451B1

公开(公告)日：2013-01-01

申请号：US12633251

申请日：2009-12-08

Applicant: Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

Inventor： Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

IPC: B64C3/00

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.

公开(公告)号：US08141822B2

公开(公告)日：2012-03-27

申请号：US11217851

申请日：2005-09-01

Applicant: James P. Thomas ,  Jared N. Baucom ,  William R. Pogue, III ,  Siddiq M. Qidwai

Inventor： James P. Thomas ,  Jared N. Baucom ,  William R. Pogue, III ,  Siddiq M. Qidwai

IPC: B64D37/02

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 two-phase liquid-gas fuel at a predetermined pressure, with a bladder outlet arranged to releasing vapor fuel from the bladder. The fuel provides energy for propulsion of the vehicle, and the vapor pressure of the fuel provides initial structural integrity of the vehicle, by rigidizing and stiffening the beam assembly to resist inward buckling until the liquid fuel is expended. In an exemplary embodiment, the vehicle is an unmanned aerial vehicle. A combustion chamber and thermoelectric conversion module can generate electricity for a propeller and battery.

Abstract translation: 一种车辆，包括至少一个用于容纳预定压力的两相液态气体燃料的气囊，其中气囊出口布置成从气囊释放蒸汽燃料。 燃料为车辆的推进提供能量，并且燃料的蒸汽压力通过刚性化和加强梁组件以抵抗向内的弯曲直到液体燃料消耗来提供车辆的初始结构完整性。 在示例性实施例中，车辆是无人驾驶飞行器。 燃烧室和热电转换模块可以为螺旋桨和电池发电。

公开(公告)号：US20100237192A1

公开(公告)日：2010-09-23

申请号：US12406173

申请日：2009-03-18

Applicant: Terry M. Sanderson ,  Rudy A. Eisentraut ,  David B. Hatfield

Inventor： Terry M. Sanderson ,  Rudy A. Eisentraut ,  David B. Hatfield

IPC: B64C3/30 ,  B64C3/38

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 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.

Abstract translation: 增强的充气翼改善了OML的公差，并加强了至少在高负载区域中的机翼。 这种方法提供具有增加的表面面积的具有翼的装备受限的空中车辆，以改善飞行耐力或空气动力学控制。 翼盒形成翼的第一部分。 具有固定到其上的多个刚性板的皮肤被充气以形成机翼的第二部分，以增加弦长或延长机翼跨度。 皮肤适当地用泡沫充气以形成固体翼。

公开(公告)号：US20080149775A1

公开(公告)日：2008-06-26

申请号：US11645029

申请日：2006-12-26

Applicant: Storm Dunker ,  Martin Gilbert

Inventor： Storm Dunker ,  Martin Gilbert

IPC: B64D17/62

CPC classification number: B64D17/62 ,  B64C39/024 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/128 ,  B64C2201/145 ,  B64D17/34

Abstract: 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.

Abstract translation: 与用于精密货物运送的降落伞的空中引导单元（AGU）一起使用的部署制动器释放系统。 降落伞包括一端固定在顶盖边缘的部署制动线，另一端通过环形端连接到电机控制线。 马达控制线又与AGU的马达接合。 部署制动器释放系统包括至少一个钩安装件，其具有固定到AGU框架上的钩子。 在索具期间，展开制动管线的环形端部与钩接合，使得在展开时，打开力被施加到钩安装件而不是马达。 在全冠层膨胀后，电机通过电机控制线拉动制动线环路端部，将其从钩上脱离，将剩余的顶盖负载转移到AGU电机，以用于其余的飞行。 还公开了一种用于释放展开制动线的方法。

公开(公告)号：US06260797B1

公开(公告)日：2001-07-17

申请号：US09229599

申请日：1999-01-13

Applicant: Miles R. Palmer

Inventor： Miles R. Palmer

IPC: B64C356

CPC classification number: F42B15/00 ,  B64C39/024 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/105 ,  B64C2201/121 ,  B64C2201/126 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/205 ,  B64D1/22 ,  B64D37/04 ,  B64D37/06 ,  B64D37/12 ,  B64D39/00

Abstract: A transformable gun launched aero vehicle having a ballistic projectile configuration and an aeroplane configuration includes a cylinder forming a shell of the vehicle in the ballistic projectile configuration and wings deployable from the cylinder. The wings are capable of achieving sufficient lift for sustained flight in the aeroplane configuration. The cylinder forms a fuselage of the vehicle in the aeroplane configuration. A wing includes plural rib elements, plural inflatable tubes where each tube is braced by the plural rib elements, and a wind shell disposed around the plural inflatable tubes and the plural rib elements. The vehicle includes an inflatable tail section that is inflated while the vehicle is in the aeroplane configuration. The vehicle includes a parachute that is reversibly deployable from a nose portion of the vehicle. The vehicle includes at least one landing rod. Each landing rod is reversibly extendable from the vehicle. A landing controller controls a first landing rod to extend after the vehicle has begun to vertically descend. The vehicle includes a folding propeller deployable from the fuselage in the aeroplane configuration. The vehicle includes a control system, and the control system includes a module to determine when the vehicle has reached a first predetermined state that defines an initiation of a transition from the ballistic projectile configuration to the aeroplane configuration.

Abstract translation: 可变形枪发射具有弹道射弹配置的航空车辆，并且飞机配置包括形成弹道射出构造的车辆壳体的气缸和从气缸展开的翼。 机翼能够在飞机配置中实现足够的升力以持续飞行。 汽缸在飞机配置中形成车辆的机身。 翼包括多个肋元件，多个可充气管，其中每个管由多个肋元件支撑，以及设置在多个可充气管和多个肋元件周围的风壳。 车辆包括在车辆处于飞机配置中时充气的可充气尾部。 车辆包括可从车辆的鼻部部分可逆地展开的降落伞。 车辆包括至少一个着陆杆。 每个着陆杆可从车辆可逆地延伸。 着陆控制器控制第一着陆杆在车辆开始垂直下降之后延伸。 该车辆包括在飞机配置中可从机身部署的折叠螺旋桨。 车辆包括控制系统，并且控制系统包括用于确定车辆何时已经达到第一预定状态的模块，该第一预定状态定义了从弹道射弹配置到飞机配置的转变的开始。

公开(公告)号：US08746620B1

公开(公告)日：2014-06-10

申请号：US13747626

申请日：2013-01-23

Applicant: Sunlight Photonics Inc.

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

IPC: B64C3/30 ,  B64C1/34

CPC classification number: B64C1/34 ,  B64C3/30 ,  B64C3/46 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/105 ,  B64C2201/122 ,  B64D2211/00 ,  H01L31/0543 ,  H02S10/40 ,  H02S20/32 ,  Y02E10/52 ,  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: 本文提供了适用于太阳能机身的方法和装置。 在一些实施例中，适应性太阳能机身包括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阳光收集和功率输出的太阳能PV系统; 以及具有空气动力学横截面的可膨胀体，该空气动力学横截面最小化在本体的任何给定厚度的寄生空气阻力，进一步包围太阳能光伏系统，并进一步包围太阳能光伏系统，并且还能够响应于 太阳能光伏系统的位置变化。

公开(公告)号：US08104713B2

公开(公告)日：2012-01-31

申请号：US12406173

申请日：2009-03-18

Applicant: Terry M. Sanderson ,  Rudy A. Eisentraut ,  David B. Hatfield

Inventor： Terry M. Sanderson ,  Rudy A. Eisentraut ,  David B. Hatfield

IPC: B64C3/54

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 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.

Abstract translation: 增强的充气翼改善了OML的公差，并加强了至少在高负载区域中的机翼。 这种方法提供具有增加的表面面积的具有翼的装备受限的空中车辆，以改善飞行耐力或空气动力学控制。 翼盒形成翼的第一部分。 具有固定到其上的多个刚性板的皮肤被充气以形成机翼的第二部分，以增加弦长或延长机翼跨度。 皮肤适当地用泡沫充气以形成固体翼。

公开(公告)号：US07377470B2

公开(公告)日：2008-05-27

申请号：US11252185

申请日：2005-10-18

Applicant: Haru Miyake

Inventor： Haru Miyake

IPC: B64C13/20

CPC classification number: B64C13/20 ,  A63H27/007 ,  A63H27/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/165

Abstract: A wireless-controlled airplane includes a flying unit and an on-ground controller which is connected to the flying unit through a communication section and flies the flying unit. The flying unit includes a body, a drive section installed on the body, a propulsion apparatus which generates a propulsive force when driven by the drive section, a main wing including a plurality of wing elements which are installed so as to be able to move with respect to each other, an opening and closing mechanism which changes the relative positions of the wing elements to change the effective area of the main wing, and a dropping apparatus which selectively holds and drops a load. By changing the effective area of the main wing, the flight speed can be changed, so the capacity and size of the drive section for rotating the propulsion apparatus can be decreased.

Abstract translation: 无线控制飞机包括飞行单元和地面控制器，其通过通信部分连接到飞行单元并飞行飞行单元。 飞行单元包括主体，安装在主体上的驱动部分，当由驱动部驱动时产生推进力的推进装置，包括多个翼元件的主翼，其安装成能够与 相对于彼此相对的改变主翼的有效面积而改变翼元件的相对位置的开闭机构，以及选择性地保持和降低载荷的下落装置。 通过改变主翼的有效面积，可以改变飞行速度，因此可以减小用于旋转推进装置的驱动部的容量和尺寸。

公开(公告)号：US07059566B2

公开(公告)日：2006-06-13

申请号：US10856360

申请日：2004-05-27

Applicant: David W. Byers ,  Gary A. Hall ,  Graham D. Hunter ,  Colen G. Kennell ,  Aleksander B. Macander ,  Judah H. Milgram ,  Jason D. Strickland

Inventor： David W. Byers ,  Gary A. Hall ,  Graham D. Hunter ,  Colen G. Kennell ,  Aleksander B. Macander ,  Judah H. Milgram ,  Jason D. Strickland

IPC: B64C1/00

CPC classification number: B64C1/068 ,  B64C1/061 ,  B64C1/22 ,  B64C3/58 ,  B64C29/02 ,  B64C31/02 ,  B64C39/024 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/105 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/185 ,  B64C2201/187 ,  B64D5/00

Abstract: A hollow elliptical-cylindrical hull conformingly houses a hollow rectangular-prismatic cabin whereby the four longitudinal parallel outside edges of the latter make contact with the inside surface of the former. The fully constructed aircraft (either non-powered or powered) includes the integral hull-plus-cabin structure along with nose, tail and airfoil structures that are coupled therewith. The cabin conformingly accommodates hollow rectangular-prismatic modules useful for cargo storage. While the nose and/or tail structure is uncoupled from the integral hull-plus-cabin structure, the modules are inserted into the cabin and the cabin is sealed. The aircraft is lifted (e.g., via airplane, helicopter, rocket or balloon) to a particular elevation and released, whereupon the two wings fully emerge and the aircraft effects controlled flight until reaching its destination. After landing, the nose and/or tail structure is uncoupled from the integral hull-plus-cabin structure, the cabin is unsealed, and the modules are removed from the cabin.

Abstract translation: 中空的椭圆柱形船体适合地容纳中空矩形棱柱舱，由此四个纵向平行的外边缘与前者的内表面接触。 完全构造的飞机（非动力或动力）包括一体的船体加舱结构以及与其结合的鼻，尾和翼型结构。 机舱适合容纳用于货物存储的中空矩形模块。 当鼻部和/或尾部结构与整体的船体 - 舱室结构脱离时，模块被插入到舱室中，舱室被密封。 飞机被提升（例如，通过飞机，直升机，火箭或气球）到特定的高度并被释放，于是两翼完全出现，并且飞机实现控制的飞行直到到达其目的地。 在着陆后，鼻部和/或尾部结构与整体式的船体 - 舱室结构脱离，舱室被开封，模块从舱室中取出。