公开(公告)号：US20050017129A1

公开(公告)日：2005-01-27

申请号：US10754251

申请日：2004-01-09

Applicant: William McDonnell

Inventor： William McDonnell

IPC: B64C25/68 ,  B64C39/02 ,  B64D3/00 ,  B64F1/02 ,  B64F1/04 ,  B64F1/10

CPC classification number: B64F1/02 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/205 ,  B64D3/00 ,  B64F1/04 ,  B64F1/10

Abstract: A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) (10). The preferred method of launch involves carrying the UAV (10) up to altitude using a parasail (8) similar to that used to carry tourists aloft. The UAV is dropped and picks up enough airspeed in the dive to perform a pull-up into level controlled flight. The preferred method of recovery is for the UAV to fly into and latch onto the parasail tow line (4) or cables hanging off the tow line and then be winched back down to the boat (2).

Abstract translation: 一种发射和检索无人机（无人机）的方法（10）。 优选的发射方法是将UAV（10）运送到高度，使用类似于用来搭载高层游客的伞（8）。 无人机被丢弃，并在潜水中获得足够的空速，执行上升到等级控制飞行。 回收的首选方法是使UAV飞入并锁定在悬挂拖线（4）上或悬挂在拖绳上的电缆，然后被绞盘回到船（2）。

公开(公告)号：US20040075018A1

公开(公告)日：2004-04-22

申请号：US10679984

申请日：2003-10-06

Applicant: Fuji Jukogyo Kabushiki Kaisha

Inventor： Akihiro Yamane

IPC: B64C011/34 ,  B64C011/44 ,  B64C027/54

CPC classification number: B64C13/20 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/165 ,  G05D1/0669 ,  G05D1/0676

Abstract: An unmanned helicopter 20 includes altitude control device for giving a command of a collective pitch rudder angle based on an altitude change rate command, etc., and performing altitude control of an airframe and takeoff device, upon reception of a takeoff start command from the ground, for causing the airframe to take off and climbing the airframe to a first altitude while increasing the collective pitch rudder angle without performing the altitude control of the altitude control device and then causing the altitude control device to start the altitude control. The unmanned helicopter further includes descending device for causing the airframe to descend to a second altitude while changing descent rate command of the altitude control device and giving a descent rate command smaller than the descent rate command to the second altitude to the altitude control device for causing the airframe to descend from the second altitude to the ground.

Abstract translation: 无人直升机20包括高度控制装置，用于基于高度变化率命令等给出集体俯仰舵角的命令，并且在从地面接收到起飞开始命令时执行机体和起飞装置的高度控制 用于使机身在不进行高度控制装置的高度控制的同时增加集体桨距方向舵角度使机身起飞并爬升到第一高度，然后使高度控制装置开始高度控制。 无人直升机进一步包括下降装置，用于使机身下降到第二高度，同时改变高度控制装置的下降速率指令，并将低于下降速率指令的下降率指令提供给第二高度，以向高度控制装置引起 机身从第二高度下降到地面。

公开(公告)号：US06685140B2

公开(公告)日：2004-02-03

申请号：US10255185

申请日：2002-09-26

Applicant: Ernest A. Carroll

Inventor： Ernest A. Carroll

IPC: B64C2556

CPC classification number: B64C39/028 ,  B64C39/024 ,  B64C2201/044 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64D17/80 ,  F02B75/34 ,  F02D35/0069 ,  F02D41/2406 ,  F02D2200/0414 ,  F02D2200/703 ,  F02D2400/06 ,  F02D2400/11 ,  G05D1/101

Abstract: A miniature, unmanned aircraft having a parachute which deploys automatically under certain conditions. The aircraft has a flight control system based on remotely generated signals, potentially achieves relatively high altitude flight for a remotely controlled aircraft, and can thus operate well beyond line-of-sight control. For safety, an automatically deployed parachute system is provided. The parachute deployment system includes a folded parachute and a propulsion system for expelling the parachute from the aircraft. Preferably, a microprocessor for flight management sends intermittent inhibitory signals to prevent unintended deployment. A deployment signal is generated, illustratively, when the microprocessor fails, when engine RPM fall below a predetermined threshold, and when the aircraft strays from predetermined altitude and course.

Abstract translation: 具有降落伞的微型无人机在某些条件下自动部署。 该飞机具有基于远程产生的信号的飞行控制系统，可能为远程控制的飞机实现相对高的高度飞行，并且因此可以远远超出视线控制。 为了安全起见，提供了自动部署的降落伞系统。 降落伞部署系统包括折叠的降落伞和用于从降落伞排出飞机的推进系统。 优选地，用于飞行管理的微处理器发送间歇性抑制信号以防止意外部署。 例如，当微处理器发生故障时，当发动机转速低于预定阈值时，以及当飞行器从预定高度和当然时间偏离时，产生部署信号。

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。