公开(公告)号：US06604706B1

公开(公告)日：2003-08-12

申请号：US09763714

申请日：2001-02-22

Applicant: Nicolae Bostan

Inventor： Nicolae Bostan

IPC: B64C2900

CPC classification number: B64C17/06 ,  B64C29/0025 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162

Abstract: An unmanned air vehicle (UAV) having a ducted fan configuration with a propeller mounted inside of an opening that extends longitudinally through a fuselage. A gyroscopic stabilization device is attached to the propeller shaft such that rotation of the propeller shaft also results in rotation of the gyroscopic stabilization device. The gyroscopic stabilization device has sufficient mass and rotates at a sufficient angular velocity such that the aircraft is gyroscopically stabilized during flight. In one embodiment, the gyroscopic stabilization device comprises a ring mounted to the outer tips of the propeller and in another embodiment is comprised of a disc.

Abstract translation: 具有风扇构造的无人驾驶飞行器（UAV），其具有安装在通过机身纵向延伸的开口内部的螺旋桨。 陀螺稳定装置连接到传动轴上，使得传动轴的旋转也导致陀螺稳定装置的旋转。 陀螺稳定装置具有足够的质量并以足够的角速度旋转，使得飞行器在飞行期间被陀螺稳定。 在一个实施例中，陀螺稳定装置包括安装到螺旋桨的外部尖端的环，并且在另一个实施例中由圆盘组成。

公开(公告)号：US06588701B2

公开(公告)日：2003-07-08

申请号：US09961447

申请日：2001-09-25

Applicant: Arie Yavnai

Inventor： Arie Yavnai

IPC: B64C2900

CPC classification number: G05D1/0038 ,  B62D57/02 ,  B62D57/04 ,  B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165 ,  G05D1/0044

Abstract: A remotely-controlled unmanned mobile device (UMD) adapted to function as a robot scout to enter and reconnoiter the site of a disaster and to communicate to a rescue mission information regarding conditions prevailing at the site, making it possible for the mission to decide on rescue measures appropriate to these conditions. The UMD is operable in either of two modes. In its air-mobility mode the UMD is able to vertically take off and land, to fly to the site and then hover thereover. In its ground-mobility mode, the UMD can walk on legs over difficult terrain and through wrecked structures and ruins. The UMD is provided with condition-sensitive sensors for gathering data regarding conditions prevailing at the site, and position-sensitive sensors for avoiding obstacles in the path of the walking UMD, thereby assuring safe mobility. Other sensors govern geo-referenced navigation and flight control functions.

公开(公告)号：US06460810B2

公开(公告)日：2002-10-08

申请号：US09878903

申请日：2001-01-22

Applicant: Terry Jack James

Inventor： Terry Jack James

IPC: G05D100

CPC classification number: B64C39/024 ,  B64C29/0025 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185

Abstract: A device for programming industry standard autopilots by unskilled pilots. The effect of the invention is such that when the invention is employed in a flying body comprising an industry standard autopilot with a digital flight control system, the invention provides for the safe operation of any aircraft by an unskilled pilot. The device additionally affords skilled pilots a more rapid and simplified means of programming autopilots while in flight thus reducing a skilled pilot's cockpit workload for all aircraft flight and directional steering, way points, and aircraft flight functions reducing the possibility of pilot error so as to effect safer flight operations of an aircraft by affording a skilled pilot to direct aircraft steering and function while under continuous autopilot control.

公开(公告)号：US20020074454A1

公开(公告)日：2002-06-20

申请号：US09738227

申请日：2000-12-15

Inventor： J. Kirston Henderson

IPC: B64D037/00

CPC classification number: B64C39/024 ,  B64C2201/082 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/123 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64D5/00 ,  B64D39/00

Abstract: A method for refueling and reloading an unmanned aircraft for continuous flight is disclosed herein wherein the unmanned aircraft is maintained and supported by a support aircraft. Both aircraft maintain cargo bays and in-flight operable doors located on the underside of each aircraft for the purposes of docking and exchanging goods. Preferably the goods comprise loadable cartridges and may contain such items as weapons, cargo, or fuel for example. In one embodiment, when both aircraft are in a docked configuration for exchange of goods during flight, the in-flight operable doors open and the support aircraft is capable of loading such cartridges aboard the unmanned aircraft. When necessary the support aircraft may load gear for the purposes of landing the unmanned aircraft. Alternate methods of reloading an unmanned aircraft for continuous flight is disclosed wherein the unmanned aircraft does not have cargo bay doors and the aircraft is supported by a support aircraft.

Abstract translation: 本文公开了一种用于加油和重新加载用于连续飞行的无人驾驶飞行器的方法，其中无人飞行器由支撑飞行器维护和支撑。 两架飞机都保持位于每架飞机下侧的货舱和飞行中可操作的门，以便对接和交换货物。 优选地，货物包括可装载的盒，并且可以包含诸如武器，货物或燃料的物品。 在一个实施例中，当两架飞机处于用于在飞行中交换货物的对接配置时，飞行中可操作的门打开，并且支撑飞机能够在无人驾驶飞机上装载这样的卡盘。 必要时，支援飞机可以为无人机着陆而装载装备。 公开了重新装载用于连续飞行的无人飞行器的替代方法，其中无人驾驶飞机没有货舱并且飞机由支撑飞机支撑。

公开(公告)号：US20020005454A1

公开(公告)日：2002-01-17

申请号：US09826424

申请日：2001-04-03

Inventor： Paul B. MacCready ,  Bart D. .Hibbs ,  Robert F. Curtin ,  Kyle D. Swanson ,  Paul Belik

IPC: B64C001/00 ,  B64B001/20 ,  B64C017/00

CPC classification number: B64D27/24 ,  B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187 ,  B64D27/02 ,  B64D37/30 ,  B64D2041/005 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44 ,  Y02T50/64 ,  Y02T90/36

Abstract: Disclosed is an aircraft, configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The aircraft includes an extendable slat at the leading edge of the wing, and a reflexed trailing edge. The aircraft comprises a flying wing extending laterally between two ends and a center point. The wing is swept and has a relatively constant chord. The aircraft also includes a power module configured to provide power via a fuel cell. The fuel cell stores liquid hydrogen as fuel, but uses gaseous hydrogen in the fuel cell. A fuel tank heater is used to control the boil-rate of the fuel in the fuel tank. The aircraft of the invention includes a support structure including a plurality of supports, where the supports form a tetrahedron that affixes to the wing.

Abstract translation: 公开了一种被配置为具有宽范围的飞行速度的飞机，在延长的时间段内消耗低水平的功率，同时以无阻碍的向下观看的方式支持通信平台。 飞机在翼的前缘包括可延伸的板条，以及反射的后缘。 飞机包括在两端之间横向延伸的飞翼和中心点。 机翼被扫掠并具有相对恒定的和弦。 该飞机还包括被配置为经由燃料电池提供电力的功率模块。 燃料电池将液态氢作为燃料储存，而在燃料电池中使用气态氢。 燃料箱加热器用于控制燃料箱中的燃料的沸腾率。 本发明的飞行器包括支撑结构，该支撑结构包括多个支撑件，其中支撑件形成固定在机翼上的四面体。

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：US06224452B1

公开(公告)日：2001-05-01

申请号：US09395706

申请日：1999-09-14

Applicant: Stewart H. Morse

Inventor： Stewart H. Morse

IPC: A63B6510

CPC classification number: A63H27/00 ,  B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162

Abstract: A radio controlled aerial disc capable of flight in any direction when airborne. The invention provides upper and lower body portions which form a disc shaped housing when connected. Within the housing there is a servo motor and drive assembly coupled to a quadripartite blade to provide lift and motion to the aerial disc. A servo control mechanism and a rear prop assembly are also components of the invention for controlling the movement of the aerial disc. A receiver mounted on the aerial disc provides a method of receiving signals from a remote transmitter to control the movement of the aerial disc.

Abstract translation: 一种无人机控制的天线，能够在空中时沿任何方向飞行。 本发明提供了连接时形成盘形壳体的上部和下部主体部分。 在壳体内部有一个伺服电机和驱动组件，它连接到四分之一刀片，以提供升降和运动到天线盘。 伺服控制机构和后支撑组件也是用于控制天线的移动的本发明的组件。 安装在天线盘上的接收机提供从远程发射机接收信号以控制天线的移动的方法。

公开(公告)号：US6086015A

公开(公告)日：2000-07-11

申请号：US307016

申请日：1999-05-07

Applicant: Paul B. MacCready, Jr.

Inventor： Paul B. MacCready, Jr.

IPC: B64C29/02 ,  B64C39/02 ,  B64D1/08 ,  B64D1/22 ,  B64C29/00

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64D1/08 ,  B64D1/22 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/165

Abstract: Apparatus for transporting a load between source and destination locations, comprising an aircraft having a body, power plant carried by the body to drive the aircraft both generally vertically and also generally horizontally, the aircraft also having a wing structure that has a leading edge remaining presented in the direction of flight; and load pick-up, carry and set-down means connected to the aircraft to elevate the load from the source location, transport the elevated and air-borne load generally horizontally, and set the load down at the destination location, the body and power plant configured for vertical flight mode to elevate and set down the load, and for generally horizontal flight mode to transport the elevated load generally horizontally below the level of the aircraft body.

Abstract translation: 用于在源和目的地之间运输负载的装置，包括具有主体的飞行器，由所述主体承载的动力装置，以大致垂直地并且大致水平地驱动飞行器，飞行器还具有保持呈现的前缘的翼结构 在飞行方向; 以及连接到飞机的负载拾取，携带和设置装置，以提高源头的负载，大体上水平地运输高空和空载负载，并将负载设置在目的地，机体和功率 配置用于垂直飞行模式的设备可提升和降低负载，并且大体上为水平飞行模式，以将升高的载荷大致水平地运送到飞机主体的水平面以下。

公开(公告)号：US5575438A

公开(公告)日：1996-11-19

申请号：US239645

申请日：1994-05-09

Applicant: Kevin P. McGonigle ,  John Ferraro ,  James P. Cycon

Inventor： Kevin P. McGonigle ,  John Ferraro ,  James P. Cycon

IPC: B64C27/10 ,  B64C27/20 ,  B64C39/02 ,  B64D47/00 ,  B64D47/08

CPC classification number: B64D47/08 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162

Abstract: An unmanned aerial vehicle (UAV) has a toroidal fuselage and a rotor assembly having a pair of counter-rotating rotors secured in fixed coaxial combination with the toroidal fuselage to provide a vertical takeoff and landing (VTOL) capability for the UAV. One embodiment of the VTOL UAV is especially configured for ground surveillance missions by the inclusion of an externally mounted, remotely controllable stowable sensor subsystem that provides an azimuthal scanning capability and a predetermined elevation/depression scanning capability to accomplish the ground surveillance mission and a foldable landing gear subsystem to facilitate landing of the VTOL UAV at unprepared ground surveillance sites.

Abstract translation: 无人飞行器（UAV）具有环形机身和转子组件，其具有与环形机身固定的同轴组合的一对反向旋转转子，以为无人机提供垂直起飞和着陆（VTOL）能力。 VTOL UAV的一个实施例通过包括外部安装的远程可控的可收缩传感器子系统特别地配置用于地面监视任务，其提供方位扫描能力和预定的仰角/凹陷扫描能力以完成地面监视任务和可折叠着陆 齿轮子系统，以便于在未准备的地面监视场所着陆无人机。

公开(公告)号：US5364230A

公开(公告)日：1994-11-15

申请号：US903061

申请日：1992-06-22

Applicant: Timothy A. Krauss ,  David H. Hunter ,  Robert D. Beatty

Inventor： Timothy A. Krauss ,  David H. Hunter ,  Robert D. Beatty

IPC: B64C27/10 ,  B64C27/12 ,  B64C27/20 ,  B64C27/33 ,  B64C27/46 ,  B64C27/605 ,  B64C39/02 ,  F02B75/02

CPC classification number: B64C27/605 ,  B64C27/20 ,  B64C27/33 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  F02B2075/025

Abstract: A rotor blade subassembly for a rotor assembly having ducted, coaxial counter-rotating rotors includes a flexbeam, an integrated torque tube/spar member, and an aerodynamic fairing or rotor blade. The flexbeam is a laminated composite structure that reacts centrifugal loads and a majority of the bending loads of the rotor assembly. The flexbeam has a spanwise predetermined linear twist so that the pretwisted flexbeam is unstrained during specified forward flight conditions. The integrated torque tube/spar member is formed as a continuous, filament wound tubular composite structure having high torsional and bending stiffness that provides a continuous torsional load path and facilitates load coupling between the rotor blade and the pretwisted flexbeam. The spar segment of the functions as the primary structural member of the rotor blade subassembly and, is operative to react all bending, torsional, shear, and centrifugal dynamic loads of the rotor assembly. The torque tube segment reacts all torsional loads and some of the bending loads of the rotor assembly. The rotor blade is fabricated from a high modulus composite material and has a high aerodynamic taper such that the tapered rotor blade has a low outboard mass, a high inboard stiffness, and a high chordwise frequency. The high chordwise frequency allows the rotor assembly to be operated over a weaker modal response zone. The tapered rotor blade includes a triangularly shaped trailing edge segment that is responsive to the aerodynamic pressures encountered during operation of the shrouded counter-rotating rotors.

Abstract translation: 具有导管的同轴反转转子的转子组件的转子叶片子组件包括柔性梁，集成的扭矩管/翼梁构件和空气动力学整流罩或转子叶片。 柔性梁是一种叠层复合结构，可使离心载荷和转子组件的大部分弯曲载荷反应。 柔性梁具有翼展方向预定的线性扭曲，使得预弯曲的柔性梁在指定的向前飞行条件下是不受约束的。 集成的扭矩管/翼梁构件形成为具有高扭转和弯曲刚度的连续的长丝缠绕管状复合结构，其提供连续的扭转载荷路径并且有助于转子叶片和预扭曲挠曲梁之间的负载耦合。 作为转子叶片子组件的主要结构构件的功能的翼梁段，可操作以对转子组件的所有弯曲，扭转，剪切和离心动态载荷作出反应。 扭矩管段对转子组件的所有扭转载荷和一些弯曲载荷作出反应。 转子叶片由高模量复合材料制成并且具有高空气动力学锥度，使得锥形转子叶片具有低的外侧质量，高的内侧刚度和高的弦向频率。 高弦弦频率允许转子组件在较弱的模态响应区域上运行。 锥形转子叶片包括三角形的后缘段，其响应于在遮蔽的反向旋转转子的操作期间遇到的空气动力学压力。