公开(公告)号：US20020030142A1

公开(公告)日：2002-03-14

申请号：US09878903

申请日：2001-01-22

Inventor： Terry Jack James

IPC: G05D001/00

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.

Abstract translation: 由不熟练的飞行员编制行业标准自动驾驶仪的设备。 本发明的效果是，当本发明用于包括具有数字飞行控制系统的行业标准自动驾驶仪的飞行器中时，本发明提供了由非技术型驾驶员对任何飞机的安全操作。 该装置另外为飞行员提供了一种更快速和简化的方式，在飞行中编程自动驾驶仪，从而减少了所有飞机飞行和定向转向，方向点和飞机飞行功能的技术飞行员驾驶舱工作量，从而降低了导频误差的可能性，从而实现 通过提供技术熟练的飞行员来指导飞机转向和在连续自动驾驶仪控制下的功能，更安全地飞行飞行。

公开(公告)号：US6056237A

公开(公告)日：2000-05-02

申请号：US882368

申请日：1997-06-25

Applicant: Richard L. K. Woodland

Inventor： Richard L. K. Woodland

IPC: B64C3/40 ,  B64C3/56 ,  B64C5/12 ,  B64C39/02 ,  B64D1/02 ,  B64D7/08 ,  B64D33/02 ,  F41G3/02 ,  F42B12/36 ,  F42B15/10 ,  F41G7/00 ,  B64C1/00

CPC classification number: B64C3/40 ,  B64C3/56 ,  B64C39/024 ,  B64C5/12 ,  B64D1/02 ,  B64D33/02 ,  B64D7/08 ,  F41G3/02 ,  F42B12/365 ,  F42B15/105 ,  F42B15/22 ,  B64C2201/046 ,  B64C2201/048 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/167 ,  B64C2201/185 ,  B64C2201/203 ,  Y02T50/145

Abstract: The present invention is generally comprised of a sonotube-compatible unmanned aerial vehicle apparatus, hereinafter referred to as a UAV, and systems for launch and control of the UAV. The UAV is generally comprised of modular sections including a nose section, a payload section, a wing and fuel tank section, and a powerplant section. The modular sections are attached to adjacent sections by uniform lock sealing rings and related components. The present invention comprises an apparatus enabling very small, man portable, ballistically launched, autonomously or semi-autonomously controlled vehicle to be deployed with preprogrammed, communicated, or telemetry mission programming. A wide range of payload packages, including emergency supplies, sensors, and antenna assemblies, may be carried, used or deployed in flight. Man-portable operation is accomplished by the use of a launch canister apparatus. The launch canister comprises retractable launch stabilizing legs, turbine engine exhaust orifices, and various antennas. The launch canister apparatus alternatively comprises a modified type "A", "B", or "C" sonotube launch canister. The system of the invention also comprises a portable Command, Control, Communications, Computer, and Intelligence (C4I) control and sensing analysis console. The console is preferably ruggedized, waterproof, shockproof, and comprises necessary control and analysis computers, input/output devices, antennas, and related hardware and software for vehicle and mission control. A C4I console and/or launch canisters may be transported by means of a backpack adapted for man portability.

Abstract translation: 本发明通常由声纳管相容的无人驾驶飞行器装置（以下称为无人机）和用于发射和控制无人机的系统组成。 无人机通常包括模块化部分，包括鼻部，有效载荷部分，机翼和燃料箱部分以及动力装置部分。 模块化部分通过均匀的锁定密封环和相关部件连接到相邻部分。 本发明包括一种能够进行预编程，通信或遥测任务编程的非常小的，便携式的，弹道发射的，自主的或半自主控制的车辆的装置。 可以在飞行中携带，使用或部署各种有效载荷包，包括应急用品，传感器和天线组件。 便携式操作通过使用发射罐装置来实现。 发射罐包括可伸缩发射稳定腿，涡轮发动机排气孔和各种天线。 发射罐装置可选地包括修改型“A”，“B”或“C”型超声波发射罐。 本发明的系统还包括便携式命令，控制，通信，计算机和智能（C4I）控制和感测分析控制台。 控制台最好是坚固耐用，防水，防震，并且包括必要的控制和分析计算机，输入/输出设备，天线以及用于车辆和任务控制的相关硬件和软件。 C4I控制台和/或发射罐可以通过适于人的便携性的背包来运输。

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。

公开(公告)号：US4659041A

公开(公告)日：1987-04-21

申请号：US784485

申请日：1985-10-04

Applicant: Juergen Dellinger ,  Ulrich Kraemer ,  Rainer Schlieske ,  Heinz Wohlers

Inventor： Juergen Dellinger ,  Ulrich Kraemer ,  Rainer Schlieske ,  Heinz Wohlers

IPC: B64D17/80

CPC classification number: B64D17/80 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/165 ,  B64C2201/185

Abstract: In an unmanned craft with a tail end propeller the improvement of a parachute landing system for causing the craft to land while being suspended by a parachute of the system; the fuselage for the craft has a rearwardly, laterally and, thus, asymmetrically arranged opening leading into a storage compartment for a pilot and a principal parachute system; a flap normally closes the opening but being openable and pivotable in outward direction about an axis being at least approximately vertical to the horizontal disposition of the craft and for about 135.degree.; a cable locks and limits the outward pivoting of the flap, acting as a rudder to steer the craft for 180.degree. during parachute deployment.

Abstract translation: 在具有尾端螺旋桨的无人驾驶技术中，降落伞着陆系统的改进使得飞行器在被系统的降落伞暂停时着陆; 机身的机身具有向后，侧向和因此不对称布置的开口，通向飞行员和主降落伞系统的储藏室; 翼片通常关闭开口，但是可以在向外的方向上围绕轴线打开和枢转，该轴线至少大致垂直于工艺的水平布置并且在约135度; 电缆锁定并限制了挡板的向外枢转，作为方向舵在降落伞部署期间将工艺转向180度。

公开(公告)号：US2636697A

公开(公告)日：1953-04-28

申请号：US23075651

申请日：1951-06-09

Applicant: LEIGH DENNY REGINALD

Inventor： LEIGH DENNY REGINALD

IPC: B64C39/02 ,  F42B4/26 ,  F42B10/56

CPC classification number: B64C39/024 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/185 ,  F42B4/26 ,  F42B10/56