公开(公告)号：US20060074557A1

公开(公告)日：2006-04-06

申请号：US11011001

申请日：2004-12-13

Applicant: Anthony Mulligan ,  Christopher Troudt ,  Jason Michael Douglas

Inventor： Anthony Mulligan ,  Christopher Troudt ,  Jason Michael Douglas

IPC: G01C21/26

CPC classification number: G05D1/0094 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/044 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/123 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/205 ,  B64C2201/208

Abstract: Methods and apparatuses provide surveillance of a convoy. At least one unmanned aerial vehicle (UAV) obtains images around the convoy's position to provide information about potential hostile activity while the UAV follows a generally curvilinear path around the convoy as instructed by one of the convoy vehicles. Path planner algorithm software is executed by the controlling convoy vehicle in which position and velocity information regarding the unmanned aerial vehicle and the convoy are processed to determine values of control variables. The determined values are sent to the unmanned aerial vehicle over a wireless communications channel. The path of the surveillance vehicle may be changed in order to provide evasive measures to avoid an attack on the surveillance vehicle by an adversary.

Abstract translation: 方法和设备对车队进行监视。 至少一架无人驾驶飞行器（UAV）获取围绕车队位置的图像，以提供关于潜在敌对行为的信息，而无人机按照车队车辆指示的方式沿着车队周围的大致曲线路径。 路径规划器算法软件由控制车队车辆执行，其中处理关于无人机和车队的位置和速度信息以确定控制变量的值。 所确定的值通过无线通信信道发送到无人驾驶飞行器。 监视车辆的路径可能会改变，以便提供回避措施，以避免对手对监控车辆的攻击。

公开(公告)号：US06923404B1

公开(公告)日：2005-08-02

申请号：US10339908

申请日：2003-01-10

Applicant: Danny D. Liu ,  Ping-Chih Chen ,  Darius Sarhaddi

Inventor： Danny D. Liu ,  Ping-Chih Chen ,  Darius Sarhaddi

IPC: B64C1/00 ,  B64C3/40 ,  B64C3/56 ,  B64C5/12 ,  B64C9/00 ,  B64C30/00 ,  B64C39/02 ,  B64C39/08 ,  B64F1/04 ,  F42B10/14 ,  F42B10/64

CPC classification number: B64F1/04 ,  B64C3/40 ,  B64C3/56 ,  B64C5/12 ,  B64C30/00 ,  B64C39/024 ,  B64C39/028 ,  B64C39/08 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/048 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/125 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  F42B10/14 ,  F42B10/64 ,  Y02T50/14

Abstract: An unmanned air vehicle (“UAV”) apparatus is configured to have a body and a body-conformal wing. The body-conformal wing is configured to variably sweep from a closed position to a fully deployed position. In the closed position, the body-conformal wing span is aligned with the body axis and in the fully deployed position the body-conformal wing span is perpendicular to the axial direction of the body. Delivery of the UAV comprises the steps of: positioning the span of a body conformal wing in alignment with the axis of the body of the UAV; initiating the flight of the UAV; and adjusting the sweep angle of the body-conformal wing as a function of the current speed, altitude, or attack angle of the UAV, with the adjustment starting at a 0 degree position and varying between a closed position and a fully deployed position. The UAV also has a control mechanism configured to variably adjust the sweep of the body-conformal wing to achieve a high lift over drag ratio through out the flight path of the UAV.

Abstract translation: 无人驾驶飞行器（“UAV”）装置被配置为具有主体和主体保形翼。 身体适形翼被配置为从关闭位置可变地扫掠到完全展开位置。 在关闭位置，身体共形翅膀跨度与身体轴线对齐，并且在完全展开位置，身体共形翅膀跨度垂直于身体的轴向。 无人机的交付包括以下步骤：将身体保形翼的跨度定位成与UAV的身体的轴线对准; 启动无人机的飞行; 并且根据UAV的当前速度，高度或攻角来调节身体保形翼的扫掠角度，调整从0度位置开始，并且在关闭位置和完全展开位置之间变化。 无人机还具有控制机构，其配置为可变地调整身体保形翼的扫掠，以通过无人机的飞行路径实现高的牵引比。

公开(公告)号：US20050029400A1

公开(公告)日：2005-02-10

申请号：US10600400

申请日：2003-06-20

Applicant: Richard Ouellette ,  Aaron Kutzmann

Inventor： Richard Ouellette ,  Aaron Kutzmann

IPC: B64C1/00 ,  B64C29/00 ,  B64C39/02 ,  B64D7/00

CPC classification number: B64C1/00 ,  B64C29/0058 ,  B64C39/024 ,  B64C2201/046 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/165 ,  B64C2201/167 ,  B64C2201/187 ,  B64D7/00

Abstract: A modular component set is configurable to form a plurality of flight capable platforms. A plurality of end pieces each has contiguously connected curved outer portions each longitudinally expanding from a tip to terminate at a blunt attachment face. Body members have opposed ends to receive the end piece blunt attachment face, and a rectangular shaped mid-portion having opposed walls. A plurality of task specific panels are each releasably connectable to one of the opposed walls. At least one of the body members with the end pieces joined at the opposed ends, and at least one of the task specific panels connected to one of the opposed walls form a minimum component set for each of the flight capable platforms.

Abstract translation: 模块化组件组可配置成形成多个具有飞行能力的平台。 多个端片各自具有连续地连接的弯曲外部部分，每个端部从尖端纵向扩展以终止于钝的附接面。 主体部件具有相对的端部以接收端部钝器附接面，以及具有相对壁的矩形中间部分。 多个任务专用面板各自可拆卸地连接到相对的壁之一。 至少一个具有端部件的主体部件在相对的端部连接，并且连接到相对的一个壁之一的任务专用面板中的至少一个为每个具有飞行能力的平台形成最小的部件组。

公开(公告)号：US20040108410A1

公开(公告)日：2004-06-10

申请号：US10309828

申请日：2002-12-04

Inventor： Henry August

IPC: B64C037/02 ,  B64D005/00

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/046 ,  B64C2201/104 ,  B64C2201/121 ,  F42B10/16 ,  F42B10/62 ,  F42B12/58 ,  F42B12/62 ,  F42B15/00

Abstract: A reusable, mach-velocity mobile platform delivers a weapons payload via vertical launch, powerless glide, weapons release, and landing operation phases. The platform includes a generally tubular shaped body having an aft and forward end, and a payload section. An arch wing is supported by the body aft end. The arch wing has an upper and a lower wing joined at distal ends by two curved end plates. A nose assembly is connected at the forward end having an upward directed fixed angle-of-attack to generate forward end lift. Thermal tiles attached under the body and the lower wing under-side radiate/dissipate heat generated during a high angle-of-attack platform reentry. Radar absorptive or radar translucent material is used. The platform preferably discharges payload from the aft end for safe separation. A landing gear is extended for the landing phase of operation.

Abstract translation: 可重复使用的马赫速度移动平台通过垂直发射，无力滑翔，武器释放和着陆操作阶段提供武器有效载荷。 平台包括具有尾部和前端的大致管状的主体和有效载荷部分。 一个弓翼由身体后端支撑。 拱翼具有通过两个弯曲端板在远端连接的上翼和下翼。 前端组件在前端连接，具有向上定向的固定迎角，以产生前端提升。 安装在车体下方的散热瓦片和下部翼片下侧辐射/消散在高角度攻角平台折返期间产生的热量。 使用雷达吸收或雷达半透明材料。 该平台优选地从尾端排出有效载荷以进行安全分离。 起落架延伸到着陆阶段。

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：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：US4765567A

公开(公告)日：1988-08-23

申请号：US24039

申请日：1987-03-10

Applicant: Meyer M. Gutman ,  Christopher N. Lash

Inventor： Meyer M. Gutman ,  Christopher N. Lash

IPC: B64C27/02 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C27/02 ,  B64C2201/024 ,  B64C2201/108 ,  B64C2201/121 ,  B64C2201/146

Abstract: A remote-controlled autogyro visually and functionally simulates a helicopter with stub wings (e.g. the Hind D), so that an expendable helicopter-simulating target is produced. The target has a fixed angle rotor shaft, the rotor being solely aerodynamically controlled. The rotor blades have a negative pitch angle, and a positive conning angle. The engine is mounted at the front of the fuselage and has a downthrust angle, and the horizontal stabilizer also slopes downwardly aft. The rotor is at about the center of lift (horizontally) of the wings, and the wing span is about 50-60 percent the length of the fuselage. The ailerons and tail rudder are electrically interconnected. Remote control is provided for the elevators ailerons, and engine speed.

Abstract translation: 视觉上和功能上模拟具有短截翼（例如Hind D）的直升机的远程控制自动扶梯，从而产生消耗性直升机模拟目标。 目标具有固定角度的转子轴，转子仅在空气动力学上被控制。 转子叶片具有负桨距角和正转角。 发动机安装在机身前部，具有推力角，水平稳定器也向下倾斜。 转子位于机翼的升降中心（水平）的左右，机翼的跨度约为机身长度的50-60％。 副翼和尾舵电气互连。 为电梯副翼提供遥控和发动机转速。

公开(公告)号：US4505442A

公开(公告)日：1985-03-19

申请号：US505815

申请日：1983-06-20

Applicant: Jerome Kirsch ,  M. Alan Kopsco ,  Edward Markow ,  Michael Sturm

Inventor： Jerome Kirsch ,  M. Alan Kopsco ,  Edward Markow ,  Michael Sturm

IPC: B63B1/28 ,  F41G7/22 ,  F42B17/00 ,  F42B23/00 ,  F41G9/00 ,  F42B15/20

CPC classification number: F42B23/00 ,  B64C25/54 ,  B64C37/00 ,  B64C39/024 ,  F41G7/22 ,  F42B17/00 ,  B63B1/322 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/121 ,  B64C2201/205 ,  Y02T70/12

Abstract: A transient surface contact vehicle for transporting a load from a surface starting point to a surface end point has a structure for carrying the load from the starting point to the end point. A vehicle support extends from the structure. A buoyancy control device mounted in the structure is coupled to the vehicle support for selectively making the support buoyant and non-buoyant whereby when the support is buoyant it abuts the surface of a body of water thereby supporting the vehicle at a predetermined distance above the surface of the body of water. An acquisition sensor mounted on the structure initiates water surface operations. A sensor is mounted on the structure and cooperates with the acquisition sensor to energize upon tracking of the target and to move the vehicle along the water surface to impact with the target at the end point. A position control mounted on the vehicle produces a negative pitching moment to maintain the structure in surface-following contact with the body of water.

Abstract translation: 用于将载荷从表面起始点传送到表面终点的瞬时表面接触车辆具有用于承载起始点到终点的载荷的结构。 车辆支架从结构延伸。 安装在结构中的浮力控制装置联接到车辆支撑件，用于选择性地使支撑件浮力和非浮力，由此当支撑件浮力时，其抵靠水体表面，从而在车辆表面上方预定的距离处支撑车辆 的身体的水。 安装在结构上的采集传感器启动水面操作。 传感器安装在结构上并与采集传感器配合，以在跟踪目标时激励并沿着水面移动车辆以在终点处与目标撞击。 安装在车辆上的位置控制产生负俯仰力矩，以保持结构与水体的表面跟随接触。

公开(公告)号：US20180251218A1

公开(公告)日：2018-09-06

申请号：US15760259

申请日：2016-09-16

Applicant: Christopher Wilkinson

Inventor： Christopher Wilkinson

IPC: B64C39/02 ,  B64D1/04

CPC classification number: B64C39/024 ,  B64C2201/02 ,  B64C2201/046 ,  B64C2201/082 ,  B64C2201/121 ,  B64C2201/123 ,  B64C2201/206 ,  B64C2201/22 ,  B64D1/04

Abstract: An unmanned aerial combat vehicle system is disclosed. The system provides for an unmanned aerial combat vehicle that is capable of performing reconnaissance, disrupting enemy communications, or delivering a weaponized payload. The unmanned aerial combat vehicle may also be equipped with a cloaking mechanism, where it can mask it's heat signature, or simulate an image on its outer surface.

公开(公告)号：US20180162527A1

公开(公告)日：2018-06-14

申请号：US15293020

申请日：2016-10-13

Applicant: THE BOEING COMPANY

Inventor： Ryan L. Hupp ,  Sean R. Wakayama

IPC: B64C39/02 ,  G05D1/00 ,  F41G9/00

CPC classification number: B64C39/024 ,  B64C2201/12 ,  B64C2201/121 ,  B64C2201/14 ,  B64C2201/146 ,  B64D7/04 ,  F41G9/002 ,  G05D1/0016 ,  G05D1/0038 ,  G05D1/0094

Abstract: An unmanned aerial system (UAS) includes a body and a lift and propulsion system coupled to the body. The UAS includes a weapon coupled to the body. The weapon has an aiming axis oriented in a fixed direction relative to the body. The UAS includes a control system operatively coupled to the lift and propulsion system and the weapon. The control system is configured to determine a roll angle and a flight path such that the aiming axis is directed at a target when the UAS moves according to at least a portion of the flight path at the roll angle. The control system is further configured to control the lift and propulsion system such that the UAS moves according to the at least the portion of the flight path at the roll angle.