公开(公告)号：US20030207164A1

公开(公告)日：2003-11-06

申请号：US10428804

申请日：2003-05-05

Applicant: ION AMERICA CORPORATION

Inventor： James Frederick McElroy ,  K.R. Sridhar

IPC: H01M008/04 ,  H01M008/18 ,  H01M008/12

CPC classification number: H01M8/186 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/101 ,  B64C2201/127 ,  B64C2201/148 ,  B64C2201/165 ,  B64D27/24 ,  B64D2041/005 ,  B64D2211/00 ,  H01M8/04007 ,  H01M8/2475 ,  H01M2250/20 ,  Y02E60/528 ,  Y02T50/44 ,  Y02T50/55 ,  Y02T50/62 ,  Y02T90/32 ,  Y02T90/36 ,  Y10S429/901

Abstract: A neutrally buoyant airship, such as a blimp, contains a lifting body which allows the airship to remain neutrally buoyant in air and a fuel cell located in the airship. A method of generating power in the neutrally buoyant airship, comprising providing a fuel and a oxidizer to a solid oxide fuel cell to generate power, and providing heat from the fuel cell to a remotely located lifting body, wherein the lifting body allows the airship to remain neutrally buoyant in air.

Abstract translation: 一个中性浮力的飞艇，如飞艇，包含一个提升机体，允许飞艇在空气中保持中性浮力，而位于飞艇上的燃料电池。 一种在中性浮力飞艇中产生动力的方法，包括向固体氧化物燃料电池提供燃料和氧化剂以产生动力，并将热量从燃料电池提供到位于远处的提升体，其中提升体允许飞艇 在空气中保持中性浮力。

公开(公告)号：US06615165B2

公开(公告)日：2003-09-02

申请号：US10255187

申请日：2002-09-26

Applicant: Ernest A. Carroll

Inventor： Ernest A. Carroll

IPC: B64C100

CPC classification number: F02D41/2406 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/044 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  F02B75/34 ,  F02D35/0069 ,  F02D2200/0414 ,  F02D2200/703 ,  F02D2400/06 ,  F02D2400/11 ,  G05D1/101

Abstract: A power and communications connection arrangement for a miniature, unmanned aircraft having data handling capability. The aircraft has a microprocessor for managing flight control, a GPS receiver, a communications radio frequency transceiver, and data handling apparatus. The latter may be any of a sensor for gathering environmental data, sensing aircraft altitude or attitude, a data relay station, or any combination of these. The data handling apparatus is part of a removable module mounted to and detachable from the aircraft. The connection arrangement includes stationary power and communications terminals fixed to the module, and corresponding free power and data cables completing respective power circuits and communications links within the aircraft. In the preferred embodiment, the microprocessor, at least one sensor, and a battery pack are located in the module, and a radio transceiver, a GPS receiver, controls such as rudder and elevator, and other sensors are located in the airframe.

Abstract translation: 一种用于具有数据处理能力的微型无人飞机的电力和通信连接装置。 飞机具有用于管理飞行控制的微处理器，GPS接收器，通信射频收发器和数据处理装置。 后者可以是用于收集环境数据，感测飞机高度或姿态，数据中继站或这些的任何组合的传感器中的任何一个。 数据处理装置是安装到飞机上并可拆卸的可拆卸模块的一部分。 连接装置包括固定电源和固定到模块的通信终端，以及相应的空闲电源和数据电缆，完成飞机内各自的电力电路和通信链路。 在优选实施例中，微处理器，至少一个传感器和电池组位于模块中，并且无线电收发器，GPS接收器，诸如方向舵和电梯以及其它传感器的控制器位于机身中。

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：US06565041B1

公开(公告)日：2003-05-20

申请号：US10028956

申请日：2001-12-27

Applicant: Eric P. Young ,  John Reynolds ,  Mathew Curran ,  Danny Gast ,  Joseph Wurts

Inventor： Eric P. Young ,  John Reynolds ,  Mathew Curran ,  Danny Gast ,  Joseph Wurts

IPC: B64D1780

CPC classification number: B64D17/40 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/165 ,  B64C2201/185 ,  B64D17/54 ,  B64D17/76 ,  B64D17/80

Abstract: A parachute system for a miniature aircraft having a storable parachute mounted on an upper surface of the aircraft. The system includes a canopy having a stored condition and an expanded condition. A plurality of suspension lines have first ends connected to the periphery of the canopy and second ends connected to an elastic member. First and second risers are connected by their first ends to the upper surface of the aircraft between the front end and center of gravity on either side of the longitudinal axis and by their second ends to the elastic member. A restraint system releasably restrains the parachute in the stored condition on the top surface of the aircraft; and a release system coupled to the restraint system releases the parachute upon command such that aerodynamic forces will cause the parachute to open.

Abstract translation: 用于具有安装在飞行器的上表面上的可存放降落伞的微型飞机的降落伞系统。 该系统包括具有存储条件和扩展状态的遮篷。 多个悬挂线具有连接到顶盖的周边的第一端和连接到弹性构件的第二端。 第一和第二立管通过其第一端连接到飞行器的上表面，在纵轴的任一侧上的前端和重心之间，并且通过其第二端连接到弹性构件。 约束系统可释放地将降落伞限制在飞机顶表面上的储存状态; 并且联接到约束系统的释放系统根据命令释放降落伞，使得空气动力将使降落伞打开。

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：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：US06170778B2

公开(公告)日：2001-01-09

申请号：US09296716

申请日：1999-04-22

Applicant: James P. Cycon ,  Mark Winfield Scott ,  Christopher W. DeWitt

Inventor： James P. Cycon ,  Mark Winfield Scott ,  Christopher W. DeWitt

IPC: B64C2730

CPC classification number: B64C27/20 ,  B64C27/10 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/165

Abstract: A method for reducing a nose-up pitching moment in an unmanned aerial vehicle during forward flight. The unmanned aerial vehicle includes counter-rotating rotor assemblies that are mounted within a duct. Each rotor assembly includes a plurality of rotor blades. The method involves adjusting the rotor blades to have substantially zero pitch. Then rotating the rotor assemblies to produce a virtual plane across the duct. The virtual plane is operative for substantially deflecting air passing over the fuselage away from the duct. In one embodiment of the invention, the method involves the further step of obstructing at least a portion of the bottom of the duct to inhibit air that is flowing across the bottom of the duct from passing into the duct.

Abstract translation: 一种用于在远程飞行期间减少无人驾驶飞行器中的起搏俯仰力矩的方法。 无人驾驶飞行器包括安装在管道内的反向旋转转子组件。 每个转子组件包括多个转子叶片。 该方法包括调整转子叶片以使其基本上为零。 然后旋转转子组件以在管道上产生虚拟平面。 虚拟平面可操作用于使穿过机身的空气基本上偏转远离管道。 在本发明的一个实施例中，该方法包括阻碍管道底部的至少一部分的进一步的步骤，以阻止流过管道底部的空气进入管道。

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：US5503350A

公开(公告)日：1996-04-02

申请号：US145204

申请日：1993-10-28

Applicant: Howard A. Foote

Inventor： Howard A. Foote

IPC: B64C39/02 ,  B64D27/24 ,  H01Q1/24

CPC classification number: G05D1/0038 ,  B64C39/024 ,  B64D27/24 ,  H01Q1/248 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/122 ,  B64C2201/165 ,  Y02T50/44 ,  Y02T50/64 ,  Y10S320/33

Abstract: An unmanned, remotely controlled microwave-powered aircraft for use as a stationary communications platform. The aircraft is generally a flying wing with a large, flat inner wing having a rectenna on the underside. Rectennas may also be provided on the underside of the wings, the combined output from the rectenna being used to provide power to two electric motors housed within torpedo-shaped nacelles which drive two rear propellers. The rectenna converts a microwave signal at 35 GHz generated by a ground power station utilizing dual gyrotrons and a 34-meter diameter antenna dish. The aircraft has a preferred airfoil cross section throughout and is constructed of lightweight but strong materials in order to provide an enhanced flying time of several months. A power management and distribution system manages the DC power produced by the rectenna to supply power to the flight controls, propulsion system and payload.

Abstract translation: 一种无人遥控的微波动力飞机，用作固定通信平台。 该飞机通常是具有大的，平坦的内翼的飞翼，其在下侧具有直角天线。 也可以在机翼的下侧设置整流器，来自整流罩的组合输出用于向容纳在用于驱动两个后部螺旋桨的鱼雷型发动机舱内的两个电动机提供动力。 整流天线使用双回旋加速器和直径34米的天线盘转换由地面电站产生的35GHz的微波信号。 该飞机具有优选的翼型横截面，并且由轻质但坚固的材料构成，以便提供几个月的增强的飞行时间。 电力管理和分配系统管理由天线产生的直流电力，为飞行控制，推进系统和有效载荷提供动力。