公开(公告)号：US06721646B2

公开(公告)日：2004-04-13

申请号：US10255184

申请日：2002-09-26

Applicant: Ernest A. Carroll

Inventor： Ernest A. Carroll

IPC: F02D4100

CPC classification number: B64D31/06 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/044 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  F02B75/34 ,  F02D35/0069 ,  F02D41/2406 ,  F02D2200/0414 ,  F02D2200/703 ,  F02D2400/06 ,  F02D2400/11 ,  Y10S123/03

Abstract: A miniature unmanned aircraft which uses remotely controlled model aircraft components and technology, and has on-board automatic “on-the-fly” fuel and air mixture adjustment enabling high altitude flight. The aircraft, which may have conventional fuselage, wing, reciprocating piston engine and radio frequency operated controls, also has sensors for sensing atmospheric pressure, atmospheric temperature, engine crankshaft rotational speed, engine temperature, and exhaust temperature. A microprocessor aboard the aircraft receives inputs from the sensors and controls at least one servo to adjust fuel and air mixture according to preprogrammed look-up tables and equations to operate the engine at appropriate fuel-to-air ratios for the altitude and other operating conditions.

Abstract translation: 一种使用遥控模型飞机部件和技术的微型无人机，并具有机载自动“飞行”燃料和空气混合调节，实现高空飞行。 可以具有常规机身，机翼，往复活塞发动机和射频操作控制器的飞行器还具有用于感测大气压力，大气温度，发动机曲轴转速，发动机温度和排气温度的传感器。 飞机上的微处理器接收来自传感器的输入并控制至少一个伺服器，以根据预编程的查找表和方程来调节燃料和空气混合物，以在适当的燃料与空气比下操作发动机的高度和其他操作条件 。

公开(公告)号：US20030234320A1

公开(公告)日：2003-12-25

申请号：US10178345

申请日：2002-06-25

Applicant: 21st Century Airships Inc.

Inventor： Hokan S. Colting

IPC: B64B001/02 ,  B64B001/06

CPC classification number: B64B1/34 ,  B64B1/02 ,  B64B1/32 ,  B64C21/02 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/101 ,  B64C2201/122 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  Y02T50/166

Abstract: An airship has a generally spherical shape and has an internal envelope for containing a lifting gas such as Helium or Hydrogen. The airship has a propulsion and control system that permits it to be flown to a desired loitering location, and to be maintained in that location for a period of time. In one embodiment the airship may achieve neutral buoyancy when the internal envelope is as little as 7% fall of lifting gas, and may have a service ceiling of about 60,000 ft. The airship has an equipment module that can include either communications equipment, or monitoring equipment, or both. The airship can be remotely controlled from a ground station. The airship has a solar cell array and electric motors of the propulsion and control system are driven by power obtained from the array. The airship also has an auxiliary power unit that can be used to drive the electric motors. The airship can have a pusher propeller that assists in driving the airship and also moves the point of flow separation of the spherical airship further aft. In one embodiment the airship can be refuelled at altitude to permit extended loitering.

Abstract translation: 飞艇具有大致球形并且具有用于容纳诸如氦气或氢气的提升气体的内部信封。 飞艇有一个推进和控制系统，允许飞行到所需的游荡地点，并在该地点保持一段时间。 在一个实施例中，当内部信封低至7％的提升气体下降时，飞艇可以实现中性浮力，并且可以具有约60,000ft的服务天花板。飞艇具有可以包括通信设备或监视的设备模块 设备，或两者兼而有之。 飞艇可以从地面站遥控。 飞艇具有太阳能电池阵列，推进和控制系统的电动机由阵列获得的功率驱动。 飞艇还具有可用于驱动电动机的辅助动力单元。 飞艇可以有一个推动螺旋桨，有助于驾驶飞艇，还可以使球形飞艇进一步向后流动。 在一个实施例中，飞艇可以在高度加油以允许延长的游荡。

公开(公告)号：US20030192985A1

公开(公告)日：2003-10-16

申请号：US10408981

申请日：2003-04-08

Inventor： Jay Lipeles

IPC: B64C001/00 ,  B64C003/00 ,  B64C005/00

CPC classification number: B64C39/024 ,  B64C3/30 ,  B64C3/56 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/105 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/203 ,  B64C2201/22 ,  B64D33/04 ,  B64D2033/045

Abstract: The Duffel Bag Airplane is an inflatable flying wing unmanned airborne vehicle (UAV). The fuselage will house everything but the wings. The wing can be rolled up around the fuselage into a small package when deflated for easy transportation, such as by being carried in a duffle bag. Fabric construction, a small internal combustion engine with cooled exhaust, and wing warping controls combine to make the airplane inexpensive and extremely stealthy. All the usual signatures have been suppressed, which allow it to be used to make observations from close range under combat conditions. Control of this airplane is accomplished by warping the wings and is supplemented with stability augmentation.

Abstract translation: Duffel Bag飞机是一种充气飞翼无人机载机（UAV）。 机身将会容纳除翅膀之外的所有东西。 机翼可以卷绕在机身周围，当放气以便于运输时，例如通过携带在行李箱中，成为一个小包装。 织物结构，具有冷却排气的小型内燃机和机翼翘曲控制相结合，使飞机廉价而且非常隐蔽。 所有通常的签名已经被压制，这允许它用于在战斗条件下从近距离观察。 这架飞机的控制是通过扭转机翼来实现的，并补充了稳定性增强。

公开(公告)号：US20030060962A1

公开(公告)日：2003-03-27

申请号：US10255184

申请日：2002-09-26

Inventor： Ernest A. Carroll

IPC: G05D001/00

CPC classification number: B64D31/06 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/044 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  F02B75/34 ,  F02D35/0069 ,  F02D41/2406 ,  F02D2200/0414 ,  F02D2200/703 ,  F02D2400/06 ,  F02D2400/11 ,  Y10S123/03

Abstract: A miniature unmanned aircraft which uses remotely controlled model aircraft components and technology, and has on-board automatic nullon-the-flynull fuel and air mixture adjustment enabling high altitude flight. The aircraft, which may have conventional fuselage, wing, reciprocating piston engine and radio frequency operated controls, also has sensors for sensing atmospheric pressure, atmospheric temperature, engine crankshaft rotational speed, engine temperature, and exhaust temperature. A microprocessor aboard the aircraft receives inputs from the sensors and controls at least one servo to adjust fuel and air mixture according to preprogrammed look-up tables and equations to operate the engine at appropriate fuel-to-air ratios for the altitude and other operating conditions.

Abstract translation: 一种使用遥控模型飞机部件和技术的微型无人机，并具有机载自动“飞行”燃料和空气混合调节，实现高空飞行。 可以具有常规机身，机翼，往复活塞发动机和射频操作控制器的飞行器还具有用于感测大气压力，大气温度，发动机曲轴转速，发动机温度和排气温度的传感器。 飞机上的微处理器接收来自传感器的输入并控制至少一个伺服器，以根据预编程的查找表和方程来调节燃料和空气混合物，以在适当的燃料与空气比下操作发动机的高度和其他操作条件 。

公开(公告)号：US20030060943A1

公开(公告)日：2003-03-27

申请号：US10255183

申请日：2002-09-26

Inventor： Ernest A. Carroll

IPC: G06F017/00

CPC classification number: G05D1/101 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/044 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  F02B75/34

Abstract: A miniature, unmanned aircraft for acquiring and/or transmitting data, capable of automatically maintaining desired airframe stability while operating by remote directional commands. The aircraft comprises a fuselage and a wing, a piston engine and propeller, a fuel supply, at least one data sensor and/or radio transceiver, a microprocessor disposed to manage flight, a radio transceiver for receiving remotely generated flight direction commands, a GPS receiver, a plurality of control surfaces and associated servomechanisms, for controlling flight stabilization and direction, roll, pitch, yaw, velocity, and altitude sensors. The microprocessor uses roll, pitch, yaw, and altitude data to control attitude and altitude of the aircraft automatically, but controls flight direction solely based on external commands. The aircraft does not exceed fifty-five pounds.

Abstract translation: 一种用于获取和/或发送数据的微型无人飞机，能够通过远程方向命令自动维持期望的机身稳定性。 飞机包括机身和机翼，活塞发动机和螺旋桨，燃料供应器，至少一个数据传感器和/或无线电收发器，被设置为管理飞行的微处理器，用于接收远程产生的飞行方向命令的无线电收发器，GPS 接收器，多个控制表面和相关联的伺服机构，用于控制飞行稳定和方向，滚动，俯仰，偏航，速度和高度传感器。 微处理器使用滚动，俯仰，偏航和高度数据来自动控制飞机的姿态和高度，但仅基于外部命令来控制飞行方向。 飞机不超过五十五磅。

公开(公告)号：US20030057327A1

公开(公告)日：2003-03-27

申请号：US10255185

申请日：2002-09-26

Inventor： Ernest A. Carroll

IPC: B64D017/00 ,  B64D019/00

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，可能为遥控飞机实现相对较高的高空飞行，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：US06502787B1

公开(公告)日：2003-01-07

申请号：US10082814

申请日：2002-02-22

Applicant: Ronald Martin Barrett

Inventor： Ronald Martin Barrett

IPC: B64C2720

CPC classification number: B64C39/024 ,  A63H27/12 ,  B64C29/02 ,  B64C39/028 ,  B64C39/062 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/162

Abstract: A vertical take-off and landing miniature aerial vehicle includes an upper fuselage segment and a lower fuselage segment that extend in opposite directions from a rotor guard assembly. A rotor rotates within the rotor guard assembly between the fuselage segments. Plural turning vanes extend from the rotor guard assembly beneath the rotor. Moreover, plural grid fins extend radially from the lower fuselage segment below the turning vanes. The aerial vehicle is capable of taking off and landing vertically. During flight, the aerial vehicle can hover and transition between a horizontal flight mode and a vertical flight mode using the grid fins.

Abstract translation: 垂直起飞和着陆的微型飞行器包括从转子保护组件沿相反方向延伸的上部机身段和下部机身段。 转子保护组件内的转子在机身段之间旋转。 多个转向叶片从转子下方的转子保护组件延伸。 而且，多个格栅翅片从转向叶片下方的下部机身段径向延伸。 飞行器能够垂直起飞和着陆。 在飞行中，飞行器可以使用网格散热片在水平飞行模式和垂直飞行模式之间悬停和转换。

公开(公告)号：US20030001045A1

公开(公告)日：2003-01-02

申请号：US09895332

申请日：2001-07-02

Applicant: ELSE Ltd.

Inventor： Aharon Yifrach

IPC: B64C003/00

CPC classification number: B64C39/024 ,  B64C3/56 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/167 ,  B64C2201/201 ,  B64D5/00 ,  Y10S244/90 ,  Y10S244/901

Abstract: An unmanned flying vehicle comprises an autonomous flying wing having at least two wing portions arranged substantially symmetrically about a center portion. Each wing portion is pivotally attached to each adjoining portion such that the wing portions are foldable for storage and openable for deployment. A preferred form is the so-called seagull wing having four wing portions. The vehicles may be programmable from a mother aircraft whilst being borne to a deployment zone using a data link which may be wireless.

公开(公告)号：US5890441A

公开(公告)日：1999-04-06

申请号：US709488

申请日：1996-09-06

Applicant: Johnny Swinson, deceased ,  by Sueanne Walker, executrix ,  Terry J. James

Inventor： Johnny Swinson, deceased ,  by Sueanne Walker, executrix ,  Terry J. James

IPC: B64C29/00 ,  B64C39/02 ,  B64C29/04

CPC classification number: B64C39/024 ,  B64C29/0025 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/185 ,  B64C2201/187

Abstract: A semiautonomously directed, autonomously controlled, gyroscopically stabilized, horizontal or vertical take off and landing (HOVTOL) flying apparatus employing two vertical lift devices equally and longitudinally spaced from the center of gravity of the apparatus; continuously integrated with a drive train apparatus, optional single or multiple power means; congruously connected thereto horizontal thrust devices. Integral to the vertical lift devices; pitch axis control devices situated at the exhaust orifices therein to vector said devices exhaust slip stream by a autonomous flight control system providing pitch stability. The autonomous flight control system providing continuously all flight control of the apparatus and said system being interfaced to a semiautonomous flight director device providing discrete flight direction function codes thereto. The combined effect of the apparatus is: When the power system rotates; coincident rotation of the drive train causes the vertical lift apparatus and horizontal thrust apparatus to counter rotate at right angles simultaneously providing both vertical lift and gyroscopic roll stability and simultaneously providing both horizontal thrust and gyroscopic yaw stability during flight; the continuous control thereof being accomplished by the autonomous flight control system and the directional steering, and function thereof in four axis effected by the semiautonomous flight director device which provides discrete flight function codes to the autonomous flight control system so as to disallow the initiation of negative flight maneuvers and/or functions providing for the safe unskilled pilot operation of the apparatus or any aircraft employing a autopilot having a autonomous digital flight control system.

Abstract translation: 使用两个垂直升降装置的半自主导向的，自主控制的，陀螺稳定的，水平或垂直的起飞和着陆（HOVTOL）飞行装置，该装置与装置的重心相等地纵向间隔开; 与传动系统设备连续集成，可选单个或多个动力装置; 一致地连接到水平推力装置。 与垂直升降装置成一体; 位于其排气孔处的俯仰轴控制装置通过提供俯仰稳定性的自主飞行控制系统向所述装置排出滑移流。 该自主飞行控制系统连续地提供装置的所有飞行控制，并且所述系统正在连接到半自主飞行指导装置，从而向其提供离散的飞行方向功能代码。 该装置的组合效果是：当电力系统旋转时; 驱动系统的一致旋转导致垂直提升装置和水平推力装置逆时针旋转，同时提供垂直提升和陀螺辊稳定性，同时在飞行期间同时提供水平推力和陀螺仪横摆稳定性; 其连续控制由自主飞行控制系统和定向转向完成，并且其功能由四通道由半自主飞行指导装置实现，该自主飞行控制系统向自主飞行控制系统提供离散飞行功能代码，从而不允许启动负 飞行机动和/或功能，提供设备的安全非技术型飞行员操作或使用具有自主数字飞行控制系统的自动驾驶仪的任何飞行器。

公开(公告)号：US5779190A

公开(公告)日：1998-07-14

申请号：US561929

申请日：1995-11-22

Applicant: James E. Rambo ,  Jerry H. Bowling ,  Robert S. Kincade

Inventor： James E. Rambo ,  Jerry H. Bowling ,  Robert S. Kincade

IPC: B64C39/02 ,  B64C1/16 ,  B64C1/26

CPC classification number: B64C39/024 ,  B64C2201/044 ,  B64C2201/104 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/203

Abstract: An unmanned aerial vehicle that includes symmetrical wings, tail section and internal compartments. The wings which include the only control surfaces can be attached to either side of the aircraft. An engine and a payload are non-symmetrically attached modules. Assembly and disassembly is performed with quick release pin and plate latches, quarter turn fasteners and guides that prevent improper assembly. The compartments include quick release hatch covers for the various internal craft compartments.

Abstract translation: 一种包括对称翅膀，尾部和内部舱室的无人驾驶飞行器。 包括唯一控制面的机翼可以安装在飞机的两侧。 发动机和有效载荷是非对称连接的模块。 装配和拆卸使用快速释放销和板闩锁，四分之一转弯紧固件和引导件进行，防止装配错误。 隔间包括各种内部舱室的快速释放舱口盖。