公开(公告)号：US20120248241A1

公开(公告)日：2012-10-04

申请号：US13430010

申请日：2012-03-26

Applicant: John Goelet

Inventor： John Goelet

IPC: B64B1/00 ,  B64C25/02 ,  B64B1/68 ,  B64B1/58

CPC classification number: B64B1/68 ,  B64B1/00 ,  B64B1/06 ,  B64B1/12 ,  B64B1/14 ,  B64B1/20 ,  B64B1/22 ,  B64B1/34 ,  B64B1/58 ,  B64B1/60 ,  B64B2201/00 ,  B64C25/32 ,  B64C25/56 ,  B64D2211/00

Abstract: An airship is provided. The airship includes a hull configured to contain a gas, at least one propulsion assembly coupled to the hull and including a propulsion device, and at least one aerodynamic component including a plurality of fairing structures including one or more slats, wherein the at least one aerodynamic component is associated with the hull and is configured to direct airflow around the airship.

Abstract translation: 提供飞艇。 飞艇包括构造成容纳气体的船体，耦合到船体的至少一个推进组件，并且包括推进装置，以及包括多个整流罩结构（包括一个或多个板条）的至少一个空气动力部件，其中所述至少一个空气动力学 组件与船体相关联，并且被配置为引导飞艇周围的气流。

公开(公告)号：US20120160959A1

公开(公告)日：2012-06-28

申请号：US13342373

申请日：2012-01-03

Applicant: Pierre Balaskovic

Inventor： Pierre Balaskovic

IPC: B64B1/00

CPC classification number: B64B1/06 ,  B64B1/10 ,  B64B1/12 ,  B64B1/30 ,  B64B1/34 ,  B64B2201/00 ,  B64C2201/00

Abstract: An airship may include a hull substantially shaped as an oblate spheroid, one or more frame members defining a support structure, wherein the support structure forms at least a partial support for the hull, at least one horizontal stabilizing member operably coupled to a lower surface of the airship, and at least one horizontal stabilizing member having a first end and a second end. The at least one horizontal stabilizing member may define an anhedral configuration. The airship may also include a vertical stabilizing member having a first end pivotally coupled to the airship and a second end oriented to remain below an upper surface of the airship. The vertical stabilizing member may be configured to pivot within a vertical plane, and the first end of the vertical stabilizing member and the first end of the at least one horizontal stabilizing member may be operably coupled to one another.

Abstract translation: 飞艇可以包括基本上成形为扁圆球体的船体，限定支撑结构的一个或多个框架构件，其中所述支撑结构至少形成用于船体的部分支撑件，至少一个水平稳定构件可操作地联接到船体的下表面 所述飞艇以及具有第一端和第二端的至少一个水平稳定构件。 所述至少一个水平稳定构件可以限定一个双面构型。 飞艇还可以包括垂直稳定构件，其具有枢转地联接到飞艇的第一端和定向成保持在飞艇的上表面下方的第二端。 垂直稳定构件可以构造成在垂直平面内枢转，并且垂直稳定构件的第一端和至少一个水平稳定构件的第一端可以可操作地彼此连接。

公开(公告)号：US20120119035A1

公开(公告)日：2012-05-17

申请号：US11919914

申请日：2006-11-27

Applicant: Issam Sharif

Inventor： Issam Sharif

IPC: B64G1/14 ,  B64B1/02

CPC classification number: B64G1/14 ,  B64B1/06 ,  B64B2201/00 ,  B64G1/002

Abstract: The invention relates to an airship which can be unfolded and folded up automatically on the ground and during flight and which can be operated as an aircraft or as a reusable space shuttle, having a combined collapsible gas cell (400), a grid network (600) which provides the shape, an aircraft body (200) comprising a cockpit (210), a cargo bay (220), a machine bay (230) and collapsible wheels (240), components for aircraft navigation control (300), two rocket motors (500L, 500R) which can be rotated, a collapsible control surface (700) and a mechanism for operation of the collapsible control surface (100). The combined collapsible gas cell (400) comprises an envelope (402) which can be folded and a housing (401) which cannot be folded. The housing (401) which cannot be folded is mounted on the inner walls and the bottom of the cargo bay (220). The gas cell (400) is filled with helium or hydrogen in the unfolded state, and is completely empty in the collapsed state. The envelope (402) which can be folded is held by the grid network (600) which provides the shape when in the unfolded state, and is located in the internal area of the housing (401), which cannot be folded, in the collapsed state.

Abstract translation: 本发明涉及一种飞艇，其能够在地面和飞行中自动展开和折叠，并且可以作为飞机或作为可重复使用的航天飞机操作，具有组合的可折叠气室（400），网格（600） ），其包括驾驶舱（210），货舱（220），机器舱（230）和可折叠轮（240），用于飞机导航控制（300）的组件，两个火箭 可旋转的电动机（500L，500R），可折叠控制表面（700）和可折叠控制表面（100）的操作机构。 组合的可折叠气室（400）包括可折叠的外壳（402）和不能折叠的外壳（401）。 不能折叠的壳体（401）安装在货舱（220）的内壁和底部上。 气体池（400）在展开状态下填充有氦气或氢气，并且在折叠状态下完全为空。 可以折叠的信封（402）由格网（600）保持，网格（600）在处于展开状态时提供形状，并且位于不能折叠的壳体（401）的内部区域中，其处于折叠状态 州。

公开(公告)号：US08104718B2

公开(公告)日：2012-01-31

申请号：US12157600

申请日：2008-06-11

Applicant: Donald Orval Shaw

Inventor： Donald Orval Shaw

IPC: B64D17/80 ,  B64D17/00 ,  B64G1/10

CPC classification number: B64C3/30 ,  B64B2201/00 ,  B64C31/036 ,  B64D27/24 ,  B64G2001/1071 ,  Y02T50/62

Abstract: The invention is an aircraft having an inflatable wing connected to a base unit, with the inflatable wing inflated with a lifting gas such as helium. The inflatable wing has a series of cell structures, and may be configured with ballonets to selectively introduce and expel outside air within the inflatable wing to vary the buoyancy and/or airfoil properties of the inflatable wing. The aircraft is particularly useful at low speeds and in thin atmospheres (such as at high Earth altitudes and on Mars), and can be used for interplanetary missions to explore planetary bodies, such as moons and planets, having atmospheres.

Abstract translation: 本发明是一种具有连接到基座单元的可充气翼的飞行器，充气翼用诸如氦气的提升气体充气。 充气翼具有一系列的细胞结构，并且可以配置有气球，以选择性地引入和排出可充气翼内的外部空气，以改变可充气翼的浮力和/或翼型性质。 该飞机在低速和薄弱的气氛（如高地球高度和火星上）特别有用，可用于行星际飞行任务，以探索具有气氛的行星体，如卫星和行星。

公开(公告)号：US20100230533A1

公开(公告)日：2010-09-16

申请号：US12404241

申请日：2009-03-13

Applicant: Douglas H. Greiner

Inventor： Douglas H. Greiner

IPC: B64B1/58 ,  B64B1/02 ,  G05D1/00

CPC classification number: B64B1/005 ,  B60V3/08 ,  B64B1/60 ,  B64B1/62 ,  B64B1/64 ,  B64B2201/00

Abstract: An airship comprising a hull configured to be inflated with a first gas; a ballonet in the hull, the ballonet configured to be inflated with a second gas that is heavier than the first gas; a fan configured to draw the second gas into the ballonet; an inflatable landing system; a duct configured in the ballonet to allow access to components in the airship; and a valve coupled to the ballonet. The valve provides a pathway for air to flow between the ballonet and a plenum chamber, the plenum chamber is formed by the airship, a landing surface, and the inflatable landing system when the inflatable landing system is in contact with the landing surface.

Abstract translation: 包括构造成用第一气体充气的船体的飞艇; 在船体中的气球，所述气球被配置为用比第一气体重的第二气体充气; 风扇，被配置为将第二气体吸入气囊; 充气着陆系统; 配置在气球中以允许进入飞艇中的部件的管道; 以及联接到气球的阀。 阀提供了一种空气在气球和增压室之间流动的通道，当充气着陆系统与着陆表面接触时，增压室由飞艇，着陆表面和可膨胀的着陆系统形成。

公开(公告)号：US07776295B2

公开(公告)日：2010-08-17

申请号：US12380729

申请日：2009-03-02

Applicant: Detlev Konigorski

Inventor： Detlev Konigorski

IPC: B01D53/34 ,  B01D53/74 ,  B64B1/00 ,  B64B1/06

CPC classification number: B64B1/20 ,  B01D53/002 ,  B01D2257/2025 ,  B01D2257/2064 ,  B01D2259/4558 ,  B64B2201/00 ,  B64C2201/022 ,  B64C2201/101 ,  B64C2201/125 ,  Y10S244/90

Abstract: An apparatus for removing harmful gas components out of the earth's atmosphere is a free-flying autonomous lightweight aircraft with an onboard gas processing system including gas separation or extraction devices, and inlets and outlets connected to the devices. Solar cells and/or thermoelectric generators provided on the craft produce electrical energy to operate the individual devices. The system may include a cryogenic closed-loop circulation system that participates in liquefying the extracted gas components. The apparatus is preferably a lighter-than-air craft like a dirigible. A method of extracting harmful gas components from the atmosphere involves flying the apparatus at a prescribed altitude level and operating the gas processing system to remove the harmful gas component from the atmosphere, then returning the apparatus to earth to offload the liquefied stored harmful gas component.

Abstract translation: 用于将有害气体成分从地球大气中除去的装置是一种自由飞行的自主轻型飞机，其具有包括气体分离或提取装置在内的气体处理系统以及连接到装置的入口和出口。 设在船上的太阳能电池和/或热电发电机产生电能来操作各个装置。 该系统可以包括参与液化提取的气体组分的低温闭环循环系统。 该装置优选地是比较轻便的轻型飞行器。 从大气中提取有害气体成分的方法包括使设备以规定的高度水平飞行，并操作气体处理系统以从大气中除去有害气体成分，然后使设备返回到地面以卸载液化的存储的有害气体成分。

公开(公告)号：US20100001128A1

公开(公告)日：2010-01-07

申请号：US12168393

申请日：2008-07-07

Applicant: John P. Morehead ,  Douglas H. Greiner ,  Renee Pasman ,  Robert R. Boyd

Inventor： John P. Morehead ,  Douglas H. Greiner ,  Renee Pasman ,  Robert R. Boyd

IPC: B60V3/08

CPC classification number: B60V3/08 ,  B64B1/06 ,  B64B1/32 ,  B64B2201/00

Abstract: A hybrid air vehicle is disclosed in which a cover is provided for a plurality of air cushioned landing pads to reduce drag when airborne. The pad is inflatable to provide an air cushioned during touchdown and deflatable during flight of the air vehicle. The cover can include a first cover portion and a second cover portion. A first cover roller of the first cover portion and a matching second cover roller of the second cover portion abut to cover the corresponding pad. The first cover roller and the second cover roller, which are separate and free from a physical linkage there between, are separable in an eyelid fashion to expose the corresponding pad. A separation gap between the first cover roller and the second cover roller is increased or decreased by roller straps to cover or expose the corresponding pad.

Abstract translation: 公开了一种混合动力车辆，其中为多个气垫着陆垫提供了一个盖子，以减少空降时的阻力。 垫子是可充气的，以便在空中飞行的飞行期间在着陆期间提供气垫并且可以充气。 盖可以包括第一盖部分和第二盖部分。 第一盖部分的第一覆盖辊和第二盖部分的匹配的第二盖辊邻接以覆盖相应的垫。 第一覆盖辊和第二覆盖辊分离并且不存在于其间的物理连接，可以以眼睑的方式分离以暴露相应的垫。 第一覆盖辊和第二覆盖辊之间的分离间隙由辊带增加或减小以覆盖或暴露相应的垫。

公开(公告)号：US07443078B1

公开(公告)日：2008-10-28

申请号：US11113472

申请日：2005-04-25

Applicant: Denyse Claire DuBrucq

Inventor： Denyse Claire DuBrucq

IPC: H01L41/08

CPC classification number: H02N2/101 ,  B63H25/24 ,  B64B2201/00 ,  B64C13/50

Abstract: This invention expands functions possible with electric equipment using charge contorting Piezo technology. We replace engines and motors with Piezo units. These power electric vehicles using nudging by Piezo strips to turn shafts or axles holding propellers or wheels. Ranges of speeds these electric air, land, and sea vehicles can go match that of gas-powered vehicles. The fuel is electrons, which are stored in circuits of rechargeable batteries laminated into their bodies and interior structure. Piezos nudge either radiating spokes or bars on squirrel cage attached to the shaft or axle rotating them at a range of speed in both directions and stopping that rotation. Steerage is achieved with Piezo trim tabs that, when charged, move the control surfaces as rudders in planes and ships, and elevators and ailerons in planes. These tabs with positive power applied change their position in one direction, and with negative power, in the other direction. Releasing gas into a section of a vehicle increases buoyancy. Piezo pumping the gas into a compressed air chamber lowers buoyancy. Using Helium for this in the aircraft allows balloon-type takeoffs and climbs. Ships with air replacing ballast water ride higher in the water. Submarines can control their depth in this same manner. Applying micro-sized Piezo pumps in a wristband, speech sounds defined by patterns of air poofs in matrix and voice pitch defined by poof frequency, gives an alternative to ear hearing for speech reception. Nano scale application of the nudge concept defines sensor output by contorting Piezos to short out power wires indicating light levels of color sensors in tri-color pixels in video cameras. Reversing the process, the Piezo units in a video display contort when signal charge defines color levels contacting power wires which power the emitters. Display brightness control is independent of this signal definition method. This method uses little power for the amount of work provided.

Abstract translation: 本发明使用电荷转换压电技术扩展了使用电气设备的功能。 我们用压电单元替换发动机和电机。 这些动力电动车辆通过压电带轻推，以转动保持螺旋桨或轮子的轴或轴。 这些电气，陆地和海上车辆的速度范围可以与气动车辆匹配。 燃料是电子，它们被储存在层叠在其体内和内部结构中的可再充电电池的电路中。 Piezos推出辐射辐条或放在安装在轴或轴上的鼠笼上的杆，它们以两个方向的速度范围旋转，并停止旋转。 使用压电调节片可以实现精确的操作，当充电时，控制面将作为方向舵移动到飞机和船舶中，电梯和副翼在飞机上。 这些具有正功率的标签在一个方向上改变它们的位置，并且在另一个方向上以负的功率改变它们的位置。 将气体释放到车辆的一部分中增加浮力。 将气体压入压缩空气室的压力降低浮力。 在飞机上使用氦气可以让气球式起飞和爬升。 用空气替代压载水的船舶在水中越高。 潜艇可以以相同的方式控制其深度。 将微型压电泵应用在腕带中，由声音模式定义的语音通过矩阵和由频率定义的语音间距来定义，可以替代耳朵听觉进行语音接收。 微型概念的纳米级应用通过扭曲Piezos定义传感器输出，以短路指示摄像机中三色像素中颜色传感器的光级别的电源线。 反转过程中，当信号电荷定义了接触为发射器供电的电源线的颜色电平时，视频显示器中的压电单元。 显示亮度控制与此信号定义方法无关。 该方法对所提供的工作量使用的功率很小。

公开(公告)号：US20080179454A1

公开(公告)日：2008-07-31

申请号：US11907883

申请日：2007-10-18

Applicant: Pierre Balaskovic

Inventor： Pierre Balaskovic

IPC: B64B1/06 ,  B64B1/08 ,  B64B1/12 ,  B64B1/24 ,  G05D1/08

CPC classification number: B64B1/06 ,  B64B1/10 ,  B64B1/12 ,  B64B1/30 ,  B64B1/34 ,  B64B2201/00 ,  B64C2201/00

Abstract: An airship may include a hull substantially shaped as an oblate spheroid, one or more frame members defining a support structure, wherein the support structure forms at least a partial support for the hull, at least one horizontal stabilizing member operably coupled to a lower surface of the airship, and at least one horizontal stabilizing member having a first end and a second end. The at least one horizontal stabilizing member may define an anhedral configuration. The airship may also include a vertical stabilizing member having a first end pivotally coupled to the airship and a second end oriented to remain below an upper surface of the airship. The vertical stabilizing member may be configured to pivot within a vertical plane, and the first end of the vertical stabilizing member and the first end of the at least one horizontal stabilizing member may be operably coupled to one another.

Abstract translation: 飞艇可以包括基本上成形为扁圆球体的船体，限定支撑结构的一个或多个框架构件，其中所述支撑结构至少形成用于船体的部分支撑件，至少一个水平稳定构件可操作地联接到船体的下表面 所述飞艇以及具有第一端和第二端的至少一个水平稳定构件。 所述至少一个水平稳定构件可以限定一个双面构型。 飞艇还可以包括垂直稳定构件，其具有枢转地联接到飞艇的第一端和定向成保持在飞艇的上表面下方的第二端。 垂直稳定构件可以构造成在垂直平面内枢转，并且垂直稳定构件的第一端和至少一个水平稳定构件的第一端可以可操作地彼此连接。

公开(公告)号：US07131613B2

公开(公告)日：2006-11-07

申请号：US10692057

申请日：2003-10-23

Applicant: Patrick D. Kelly

Inventor： Patrick D. Kelly

IPC: B64C39/02

CPC classification number: B64G1/005 ,  B64B1/20 ,  B64B1/30 ,  B64B2201/00

Abstract: A system is disclosed for lifting a rocket into the upper atmosphere and establishing forward flight at several hundred miles per hour, before the rocket engines are ignited and the rocket is released from the lifting system. The main subassemblies of this lifting system comprise: (1) an array of large helium-filled dirigibles, of a size that can provide hundreds or thousands of tons of lifting force; (2) a tank-holding assembly that will be tethered to the dirigibles, and that will contain pumps and high-pressure tanks, to recapture and store the helium for use in subsequent launches; and, (3) a winged platform, with wings that can be rotated vertically during liftoff, and horizontally to establish forward flight after a desired altitude has been reached, and having conventional aircraft engines on each wing. This system enables safer, less expensive, and more efficient launching of rockets and heavy payloads into space, using easily reusable subassemblies.

Abstract translation: 公开了一种系统，用于在火箭发动机被点燃并且火箭从提升系统释放之前将火箭提升到上部大气中并建立每小时几百英里的向前飞行。 该提升系统的主要组件包括：（1）大型氦气填充的可拆装的阵列，其尺寸可以提供数百或数千吨的提升力; （2）将连接到可拆卸的储罐组件，并将包含泵和高压罐，以重新捕获和存储氦气以用于随后的发射; 和（3）翼形平台，具有能够在起飞期间垂直旋转的翼，并且在达到期望的高度之后水平地建立向前飞行，并且在每个翼上具有常规的飞机发动机。 该系统使用易于重复使用的组件，可以更安全，更便宜，更有效地将火箭和重型有效载荷发射到太空。