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公开(公告)号：US08536501B2
公开(公告)日：2013-09-17
申请号：US10692039
申请日：2003-10-22
申请人： Minas Tanielian
发明人： Minas Tanielian
CPC分类号： B64C39/024 , B64C2201/022 , B64C2201/027 , B64C2201/042 , B64C2201/084 , B64C2201/101 , B64C2201/108 , B64C2201/127 , B64C2201/128 , B64C2201/146 , B64C2201/162 , B64C2201/208 , B64D2211/00 , G05D1/0022 , H02J7/025 , H02J17/00 , H02J50/30 , H02J50/50 , H02J50/90 , Y02T50/55
摘要： The present invention provides a position control system for a remote-controlled vehicle, a vehicle operated by the control system, and a method for operating a remote-controlled vehicle. An electromagnetic energy receiver is configured to receive an electromagnetic beam. The electromagnetic energy receiver is further configured to determine a position of the remote-controlled vehicle relative to a position of the electromagnetic beam. The vehicle is directed to maneuver to track the position of the electromagnetic beam.
摘要翻译： 本发明提供了一种用于遥控车辆的位置控制系统，由控制系统操作的车辆以及用于操作遥控车辆的方法。 电磁能量接收器被配置为接收电磁波束。 电磁能量接收器还被配置为确定遥控车辆相对于电磁波束的位置的位置。 车辆被引导以操纵以跟踪电磁波束的位置。
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公开(公告)号：US20120248241A1
公开(公告)日：2012-10-04
申请号：US13430010
申请日：2012-03-26
申请人： John Goelet
发明人： John Goelet
CPC分类号： 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
摘要： 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.
摘要翻译： 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。
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公开(公告)号：US08226025B2
公开(公告)日：2012-07-24
申请号：US13299883
申请日：2011-11-18
申请人： Martin L. Gomez , Robert Parks , Adam J. Woodworth
发明人： Martin L. Gomez , Robert Parks , Adam J. Woodworth
CPC分类号： B64C37/02 , B64C23/076 , B64C39/024 , B64D2211/00 , Y02T50/164 , Y02T50/55
摘要： A system and method for docking various types of aircraft is disclosed. An aerodynamic lifting structure docking mechanism for docking two or more aircraft is provided comprising an aerodynamic lifting structure. The aerodynamic lifting structure includes a first and second airflow adjustment mechanism. The aerodynamic lifting structure further includes a first hard docking mechanism, and a second hard docking mechanism, and still further includes a soft docking mechanism. The first and second airflow adjustment mechanisms are configured to substantially remove any aerodynamic lifting structure vortices around each of the aerodynamic lifting structure tip areas. The soft docking mechanism is configured to soft dock a first aerodynamic lifting structure with a second aerodynamic lifting structure. The first hard docking mechanism is configured to hard dock with the second hard docking mechanism, thereby temporarily attaching the first aerodynamic lifting structure with the second aerodynamic lifting structure.
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公开(公告)号：US20120061506A1
公开(公告)日：2012-03-15
申请号：US13299924
申请日：2011-11-18
申请人： MARTIN L. GOMEZ , ROBERT PARKS , ADAM J. WOODWORTH
发明人： MARTIN L. GOMEZ , ROBERT PARKS , ADAM J. WOODWORTH
IPC分类号： B64C37/02
CPC分类号： B64C37/02 , B64C23/076 , B64C39/024 , B64D2211/00 , Y02T50/164 , Y02T50/55
摘要： A system and method for docking various types of aircraft is disclosed. An aerodynamic lifting structure docking mechanism for docking two or more aircraft is provided comprising an aerodynamic lifting structure. The aerodynamic lifting structure includes a first and second airflow adjustment mechanism. The aerodynamic lifting structure further includes a first hard docking mechanism, and a second hard docking mechanism, and still further includes a soft docking mechanism. The first and second airflow adjustment mechanisms are configured to substantially remove any aerodynamic lifting structure vortices around each of the aerodynamic lifting structure tip areas. The soft docking mechanism is configured to soft dock a first aerodynamic lifting structure with a second aerodynamic lifting structure. The first hard docking mechanism is configured to hard dock with the second hard docking mechanism, thereby temporarily attaching the first aerodynamic lifting structure with the second aerodynamic lifting structure.
摘要翻译： 公开了用于对接各种类型的飞机的系统和方法。 提供了用于对接两个或更多个飞行器的空气动力提升结构对接机构，其包括空气动力提升结构。 空气动力提升结构包括第一和第二气流调节机构。 空气动力提升结构还包括第一硬对接机构和第二硬对接机构，并且还包括软对接机构。 第一和第二气流调节机构构造成基本上去除围绕每个空气动力提升结构尖端区域的任何空气动力学提升结构涡流。 柔性对接机构被配置为使第一空气动力提升结构与第二空气动力提升结构软对接。 第一硬对接机构构造成与第二硬对接机构硬地对接，从而将第一空气动力提升结构临时附接到第二空气动力提升结构。
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公开(公告)号：US08061646B2
公开(公告)日：2011-11-22
申请号：US12210711
申请日：2008-09-15
申请人： Martin L. Gomez , Robert Parks , Adam J. Woodworth
发明人： Martin L. Gomez , Robert Parks , Adam J. Woodworth
CPC分类号： B64C37/02 , B64C23/076 , B64C39/024 , B64D2211/00 , Y02T50/164 , Y02T50/55
摘要： A system and method for docking various types of aircraft is disclosed. An aerodynamic lifting structure docking mechanism for docking two or more aircraft is provided comprising an aerodynamic lifting structure. The aerodynamic lifting structure includes a first and second airflow adjustment mechanism. The aerodynamic lifting structure further includes a first hard docking mechanism, and a second hard docking mechanism, and still further includes a soft docking mechanism. The first and second airflow adjustment mechanisms are configured to substantially remove any aerodynamic lifting structure vortices around each of the aerodynamic lifting structure tip areas. The soft docking mechanism is configured to soft dock a first aerodynamic lifting structure with a second aerodynamic lifting structure. The first hard docking mechanism is configured to hard dock with the second hard docking mechanism, thereby temporarily attaching the first aerodynamic lifting structure with the second aerodynamic lifting structure.
摘要翻译： 公开了用于对接各种类型的飞机的系统和方法。 提供了用于对接两个或更多个飞行器的空气动力提升结构对接机构，其包括空气动力提升结构。 空气动力提升结构包括第一和第二气流调节机构。 空气动力提升结构还包括第一硬对接机构和第二硬对接机构，并且还包括软对接机构。 第一和第二气流调节机构构造成基本上去除围绕每个空气动力提升结构尖端区域的任何空气动力学提升结构涡流。 柔性对接机构被配置为使第一空气动力提升结构与第二空气动力提升结构软对接。 第一硬对接机构构造成与第二硬对接机构硬地对接，从而将第一空气动力提升结构临时附接到第二空气动力提升结构。
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公开(公告)号：US08002216B2
公开(公告)日：2011-08-23
申请号：US12139402
申请日：2008-06-13
申请人： Darwin Kent Decker
发明人： Darwin Kent Decker
CPC分类号： B64D27/24 , B64C11/305 , B64C17/06 , B64C39/10 , B64C2201/028 , B64C2201/042 , B64C2201/141 , B64C2201/146 , B64C2201/165 , B64D2211/00 , F02K5/00 , Y02T50/12 , Y02T50/44 , Y02T50/55 , Y02T50/62
摘要： A solar powered air vehicle that can stay aloft for indefinite periods of time. The vehicle employs photovoltaic solar cells for primary power and high speed counter-rotating flywheels for energy storage and steering of the vehicle. The flywheels are placed in the wing to reduce airfoil drag. A control law provides three-axis stabilized control of the vehicle by controlling propeller pitch to vary the speeds of the flywheels.
摘要翻译： 太阳能动力的空中飞行器，可以在高处保持无限期的时间。 车辆采用光伏太阳能电池用于主电力和高速反向旋转飞轮，用于车辆的储能和转向。 飞轮放置在机翼中以减少机翼拖动。 控制规则通过控制螺旋桨桨距来改变飞轮的速度来提供对车辆的三轴稳定控制。
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公开(公告)号：US07802756B2
公开(公告)日：2010-09-28
申请号：US11732109
申请日：2007-04-02
申请人： Greg T. Kendall , Walter R. Morgan
发明人： Greg T. Kendall , Walter R. Morgan
IPC分类号： B64C3/38
CPC分类号： B64C3/38 , B64C3/42 , B64C3/52 , B64C15/02 , B64C17/00 , B64C39/024 , B64C39/10 , B64C2201/028 , B64C2201/042 , B64C2201/102 , B64C2201/122 , B64C2201/126 , B64C2201/127 , B64C2201/146 , B64C2201/165 , B64D27/24 , B64D31/06 , B64D2211/00 , H04B7/18504 , Y02T50/12 , Y02T50/14 , Y02T50/44 , Y02T50/55
摘要： A span-loaded, highly flexible flying wing, having horizontal control surfaces mounted aft of the wing on extended beams to form local pitch-control devices. Each of five spanwise wing segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other wing segments, to minimize inter-segment loads. Wing dihedral is controlled by separately controlling the local pitch-control devices consisting of a control surface on a boom, such that inboard and outboard wing segment pitch changes relative to each other, and thus relative inboard and outboard lift is varied.
摘要翻译： 跨度加载，高度灵活的飞翼，具有安装在延伸梁上的机翼后部的水平控制表面，以形成局部俯仰控制装置。 机翼的五个翼展翼段中的每一个具有一个或多个电动机和光伏阵列，并且独立于其它翼段产生其自己的电梯，以最小化段间负载。 翼形二面体通过单独控制由悬臂上的控制表面组成的局部俯仰控制装置来控制，使得内侧和外侧翼段节距相对于彼此变化，因此相对的内侧和外侧升力变化。
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公开(公告)号：US20100055512A1
公开(公告)日：2010-03-04
申请号：US12589914
申请日：2009-10-30
IPC分类号： H01M8/00
CPC分类号： B64D27/24 , B64C2201/042 , B64D2041/005 , B64D2211/00 , H01M8/04097 , H01M8/04164 , H01M8/04373 , H01M8/04768 , H01M8/0656 , H01M8/186 , Y02E60/368 , Y02E60/528 , Y02P20/134 , Y02T50/44 , Y02T50/55 , Y02T50/62 , Y02T90/36
摘要： A closed loop energy storage system configured with a hydrogen tank, an oxygen tank, a fuel cell stack and an electrolyzer. A heat exchanger freeze-dries the hydrogen and oxygen prior to their storage in their respective tanks. The heat exchanger also uses excess fuel cell heat to preheat streams of hydrogen and oxygen coming from the tanks. Phase separators serve both to separate water from hydrogen and oxygen, and to store the water. A thermal management system encloses all the system components except the tanks. An airfoil-shaped shell covers the system, and the larger of the two tanks extends substantially across the shell at its point of greatest camber thickness. The tanks are composed of polymer liners integral with composite shells.
摘要翻译： 一种闭环储能系统，其配置有氢罐，氧气罐，燃料电池堆和电解槽。 热交换器在将氢气和氧气储存在各自的储罐中之前将其冷冻干燥。 热交换器还使用过量的燃料电池热来预热来自罐的氢气和氧气流。 相分离器用于将水与氢气和氧气分开，并储存水分。 一个热管理系统包含除坦克之外的所有系统组件。 翼型壳体覆盖系统，并且两个坦克中的较大的壳体在其最大外倾厚度的点处基本上延伸穿过壳体。 这些罐由聚合物衬垫组成，与复合壳一体。
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29.发明授权公开(公告)号：US07653464B1
公开(公告)日：2010-01-26
申请号：US11398738
申请日：2006-04-04
申请人： Atindra K. Mitra
发明人： Atindra K. Mitra
IPC分类号： G01C23/00
CPC分类号： B60W20/00 , B60K6/105 , B60K16/00 , B60K2016/006 , B64C39/024 , B64C2201/024 , B64D27/24 , B64D2211/00 , F03D9/00 , F03D9/25 , F05B2240/941 , G01C23/00 , H02S10/12 , Y02E10/725 , Y02T10/6204 , Y02T10/90 , Y02T50/44 , Y02T50/55 , Y02T50/64
摘要： A hybrid air-ground vehicle design that cycles through a regenerative energy phase during a ground-based trajectory. The regenerative ground-based trajectory, in turn, produces energy for purposes of implementing another air-based trajectory cycle. The design significantly improves the versatility and endurance of robotic position-adaptive sensor designs. The radar (or electro-optic) sensors on the platform perform surveillance operations during both the ground and air trajectories of the hybrid air/ground vehicle.
摘要翻译： 一种在地面轨迹中循环通过再生能量相的混合空中地面车辆设计。 为了实现另一个基于空气的轨迹循环，再生地面轨迹又产生能量。 该设计显着提高了机器人位置自适应传感器设计的通用性和耐用性。 平台上的雷达（或电光）传感器在混合空气/地面车辆的地面和空中轨迹进行监视操作。
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公开(公告)号：US20090292407A1
公开(公告)日：2009-11-26
申请号：US12471094
申请日：2009-05-22
申请人： Robert J. Minelli , Stephen Haase , Richard Kutyn
发明人： Robert J. Minelli , Stephen Haase , Richard Kutyn
CPC分类号： B64D27/24 , B64C27/26 , B64C2201/028 , B64C2201/042 , B64C2201/108 , B64C2201/165 , B64D2211/00 , H01M8/18 , Y02E60/528 , Y02T50/55 , Y02T50/62
摘要： A solar-powered aircraft having a rotating tail assembly and/or a fore assembly is provided. The tail and fore assemblies have solar cells mounted on their upper surfaces and are rotated during flight to track the sun.
摘要翻译： 提供具有旋转尾部组件和/或前组件的太阳能飞行器。 尾部和前部组件具有安装在其上表面上的太阳能电池并且在飞行期间旋转以跟踪太阳。
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