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公开(公告)号：US20180155005A1
公开(公告)日：2018-06-07
申请号：US15706807
申请日：2017-09-18
申请人： AeroVironment, Inc.
IPC分类号： B64C3/38 , H04B7/185 , B64C17/00 , B64D31/06 , B64C39/10 , B64C15/02 , B64C3/52 , B64D27/24 , B64C39/02 , B64C3/42
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.
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公开(公告)号：US20180134381A1
公开(公告)日：2018-05-17
申请号：US15816319
申请日：2017-11-17
发明人： Jon Rimanelli , Lai YIZHANG
CPC分类号： B64C29/0033 , B64C25/34 , B64C25/405 , B64C37/00 , B64C39/024 , B64C2201/027 , B64C2201/042 , B64C2201/066 , B64C2201/088 , B64C2201/102 , B64C2201/108 , B64C2201/127 , B64C2201/128 , B64C2201/146 , B64C2201/162 , B64D9/00 , B64D47/08 , B64D2211/00 , Y02T50/55
摘要： An unmanned air vehicle is provided. The unmanned air vehicle includes a frame having a center portion connecting two substantially parallel transversely spaced apart ele-wings. The ele-wings may store batteries and rotate along a forward axis to provide lift during a transition from vertical flight to linear flight. The landing gear may be connected to the ele-wings and configured to change pitch of the ele-wing to ensure stable flight during flight mode transition. A plurality of propellers, each having propeller drive motors, are attached to the frame and able to rotate from parallel position, relative to the center portion, for vertical flight to a perpendicular position, relative to the center portion, for linear flight. The propeller drives rotate on its axis and may be configured to propel the vehicle in a ground and flight mode.
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公开(公告)号：US20160185459A1
公开(公告)日：2016-06-30
申请号：US14654181
申请日：2013-12-18
发明人： Andreas KIEFER , Jens FEDERHEN , Dieter DRAGON , Werner SCHOLZ
CPC分类号： B64D27/26 , B64C39/024 , B64C2201/042 , B64C2201/082 , B64C2201/122 , B64D5/00 , B64D27/02 , B64D27/24 , B64D41/00 , B64D2211/00 , Y02T50/44 , Y02T50/55 , Y02T50/62
摘要： An auxiliary device is provided for a high-altitude airplane. The auxiliary device includes a drive, which is independent of the airplane, for the ascent of the airplane into the stratosphere. The airplane is releasably coupled to the auxiliary device. The auxiliary drive is releasable from the airplane altitude on the latest on reaching a predetermined mission.
摘要翻译： 为高空飞机提供辅助装置。 辅助装置包括独立于飞机的驱动器，用于使飞机上升到平流层。 飞机可释放地联接到辅助装置。 辅助驱动器在达到预定任务时可从最近的飞机高度释放。
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公开(公告)号：US20160068252A1
公开(公告)日：2016-03-10
申请号：US14838297
申请日：2015-08-27
申请人： AeroVironment Inc.
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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5.发明申请LIFTING ENTRY/ATMOSPHERIC FLIGHT (LEAF) UNIFIED PLATFORM FOR ULTRA-LOW BALLISTIC COEFFICIENT ATMOSPHERIC ENTRY AND MANEUVERABLE ATMOSPHERIC FLIGHT AT SOLAR SYSTEM BODIES 审中-公开提升进入/大气飞行（LEAF）统一的平台，用于超低温度系统大气入口和可转换的太阳系系统大气层飞行公开(公告)号：US20150210407A1
公开(公告)日：2015-07-30
申请号：US14297370
申请日：2014-06-05
发明人： KRISTEN S. GRIFFIN , JON CARPENTER , GREGORY J. LEE , AMY LO , RONALD POLIDAN , DANIEL SOKOL , BARNABY WAINFAN , WARREN JAMES , DENNIS POULOS
CPC分类号： B64G1/62 , B64B1/12 , B64B1/20 , B64B1/24 , B64B2201/00 , B64D2211/00 , B64G1/007 , B64G1/242 , B64G2001/1064 , B64G2001/224 , Y02T50/55
摘要： An aerial vehicle including a collapsible and inflatable vehicle body capable of being filled with a lighter than air gas so as to make the vehicle semi-buoyant or 100% buoyant at a predetermined altitude in an atmosphere above a solar system body. The vehicle body has a shape suitable to provide aerodynamic lift. The vehicle may include a propulsion device coupled to and extending from the vehicle body, where the device provides power to aerodynamically lift the vehicle above the 100% buoyant altitude to a higher altitude where the vehicle can maintain that altitude through the aerodynamic lift and vehicle buoyancy. The vehicle is configured to be deployed/inflated from a collapsed and stowed configuration to a deployed/inflated configuration in an orbit above the atmosphere of the solar system body, and is configured to enter the atmosphere in the inflated configuration and descend without propulsion.
摘要翻译： 一种飞行器，其包括可折叠且可充气的车身，其能够充满比空气更轻的车辆，以使得车辆在太阳系体上方的气氛中在预定高度上半浮力或100％浮力。 车体具有适于提供气动升力的形状。 车辆可以包括联接到车身并从车身延伸的推进装置，其中该装置提供动力以将车辆空气动力地提升到高于100％浮力高度的高度，其中车辆可以通过空气动力升力和车辆浮力保持高度 。 车辆被构造成从塌陷和收起的构造展开/充气到位于太阳系体内的空气上方的轨道上的展开/膨胀构造，并且被构造成以膨胀构型进入大气并且不推动下降。
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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：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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