公开(公告)号：US07066430B2

公开(公告)日：2006-06-27

申请号：US10758956

申请日：2004-01-16

Applicant: Brian D. Dennis ,  Clifford Jackson ,  Brian T. McGeer ,  Andreas H. von Flotow

Inventor： Brian D. Dennis ,  Clifford Jackson ,  Brian T. McGeer ,  Andreas H. von Flotow

IPC: B64F1/02

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64C2201/205 ,  B64F1/06 ,  B64F1/222

Abstract: Methods and apparatuses for capturing and recovering unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be captured at an extendable boom. The boom can be extended to deploy a recovery line to retrieve the aircraft in flight. The boom can be retracted when not in use to reduce the volume it occupies. A tension device coupled to the recovery line can absorb forces associated with the impact of the aircraft and the recovery line.

Abstract translation: 描述了用于捕获和恢复无人驾驶飞机和其他飞行装置或射弹的方法和装置。 在一个实施例中，飞机可以在可延伸的吊杆上被捕获。 可以扩展繁荣部署恢复线以在飞行中检索飞机。 当不使用吊杆时，可以收起吊杆，以减少其占用的体积。 耦合到回收管线的张紧装置可以吸收与飞机和回收管线的冲击相关联的力。

公开(公告)号：US20060006281A1

公开(公告)日：2006-01-12

申请号：US11098529

申请日：2005-04-05

Applicant: Omri Sirkis

Inventor： Omri Sirkis

IPC: B64C25/56

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/167 ,  B64C2201/187

Abstract: There is provided an Unmanned Air Vehicle (UAV) including an engine and an airframe, including means for performing a deep stall maneouvre; at least one inflatable sleeve connected or connectable to the airframe, and means for inflating the sleeve during flight, wherein the inflated sleeve extends along the lower side of the airframe so as to protect same during deep stall landing. A method for operating an Unmanned Air Vehicle (UAV), including an engine and an airframe is also provided.

Abstract translation: 提供了包括发动机和机身在内的无人机（UAV），其中包括进行深层失速行动的手段; 连接或连接到机身的至少一个可充气套筒，以及用于在飞行期间使套筒充气的装置，其中，所述膨胀的套筒沿着机身的下侧延伸，以便在深度失速着陆期间保护该套筒。 还提供了一种用于操作无人机（UAV）的方法，包括发动机和机身。

公开(公告)号：US20050151010A1

公开(公告)日：2005-07-14

申请号：US10769304

申请日：2004-01-30

Applicant: Masaki Hamamoto ,  Yoshiji Ohta ,  Keita Hara

Inventor： Masaki Hamamoto ,  Yoshiji Ohta ,  Keita Hara

IPC: B25J5/00 ,  B64C33/02 ,  B64C39/02 ,  H02N2/00

CPC classification number: B64C33/02 ,  B64C39/028 ,  B64C2201/025 ,  B64C2201/044 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146

Abstract: On a main body portion of a fluttering apparatus, a wing (left wing) is formed which has a front wing shaft, a rear wing shaft and a wing film provided spreading over the front and rear wing shafts. Further, on the main body portion, a rotary actuator for driving the front wing shaft and a rotary actuator for: driving the rear wing shaft are mounted. The front (rear) wing shafts reciprocate in a plane orthogonally crossing an axis of rotation with the actuator serving as the fulcrum. Thus, a moving apparatus is obtained which has superior maneuverability and can move not hindered by any obstacle or geometry both indoors and outdoors.

Abstract translation: 在飘动装置的主体部分上，形成有一个翼翼（左翼），其具有前翼轴，后翼轴和设置在前翼和后翼轴上的翼片。 此外，在主体部分上安装有用于驱动前翼轴的旋转致动器和用于驱动后翼轴的旋转致动器。 前（后）翼轴在与作为支点的致动器正交的旋转轴线的平面中往复运动。 因此，获得具有优异的机动性并且可以在室内和室外不受任何障碍物或几何形状阻碍的移动装置。

公开(公告)号：US06892981B2

公开(公告)日：2005-05-17

申请号：US10408981

申请日：2003-04-08

Applicant: Jay Lipeles

Inventor： Jay Lipeles

IPC: B64C3/30 ,  B64C3/56 ,  B64C39/02 ,  B64C39/10 ,  B64D33/04 ,  B64C39/00

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：US20050093507A1

公开(公告)日：2005-05-05

申请号：US10976566

申请日：2004-10-29

Applicant: Steven Sliwa ,  Andreas von Flotow ,  Brian Dennis

Inventor： Steven Sliwa ,  Andreas von Flotow ,  Brian Dennis

IPC: B63H20060101 ,  B64C11/00 ,  B64C11/04 ,  B64C11/14 ,  B64C11/28 ,  B64C39/02 ,  B64D41/00 ,  F02K5/02 ,  H02J7/00

CPC classification number: B64C11/003 ,  A63H27/02 ,  B64C11/04 ,  B64C11/14 ,  B64C11/28 ,  B64C39/024 ,  B64C2201/044 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64C2201/206 ,  B64D41/007 ,  F02K5/023 ,  F05D2260/85 ,  Y02T50/44 ,  Y02T50/672

Abstract: Methods and systems for starting propeller driven aircraft and other devices are disclosed. A system in accordance with one embodiment of the invention includes a removable fixture that is coupled to the propeller and has at least one portion exposed to a flowstream to rotate the propeller during engine start-up. The fixture is configured to separate from the propeller after the engine begins to turn over (e.g., after the engine starts and/or rotates above a threshold rate). Accordingly, the system can include a releasable link between the fixture and the propeller.

Abstract translation: 公开了用于启动螺旋桨驱动的飞机和其他装置的方法和系统。 根据本发明的一个实施例的系统包括可拆卸的固定装置，其连接到螺旋桨并且具有暴露于流动流中的至少一个部分以在发动机起动期间旋转螺旋桨。 发动机开始翻转（例如在发动机起动和/或旋转高于阈值速率之后），该固定装置构造成与螺旋桨分离。 因此，系统可以包括夹具和螺旋桨之间的可释放的连接。

公开(公告)号：US20040129833A1

公开(公告)日：2004-07-08

申请号：US10626697

申请日：2003-07-25

Applicant: C.R.F. SOCIETA CONSORTILE PER AZIONI

Inventor： Piero Perlo ,  Denis Bollea ,  Roberto Finizio ,  Cosimo Carvignese ,  Elena Balocco

IPC: B64C039/00

CPC classification number: B64C29/02 ,  B64C27/20 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165

Abstract: VTOL micro-aircraft comprising a first and a second ducted rotor mutually aligned and distanced according to a common axis and whose propellers are driven in rotation in mutually opposite directions. Between the two ducted rotors are positioned a fuselage and a wing system formed by wing profiles forming an X or an H configuration and provided with control flaps.

Abstract translation: VTOL微型飞机包括第一和第二导管转子，该第一和第二导管转子根据公共轴相互对准和间隔，并且其螺旋桨沿彼此相反的方向旋转驱动。 在两个管状转子之间设置有由机翼轮廓形成的机身和机翼系统，所述机翼轮廓形成X或H构造并设置有控制翼片。

公开(公告)号：US06634593B2

公开(公告)日：2003-10-21

申请号：US10218885

申请日：2002-08-14

Applicant: Marc Lepretre ,  Georges Chastang

Inventor： Marc Lepretre ,  Georges Chastang

IPC: B64C2720

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165

Abstract: The invention concerns a remote-controlled flying machine, in particular for surveillance and inspection, capable of hovering and comprising a spherical open-worked resistant shroud integral with a cylindrical fairing wherein rotates a propeller powered by an engine housed in a fuselage secured to the fairing with radial arms and straightening vanes.

公开(公告)号：US20020193914A1

公开(公告)日：2002-12-19

申请号：US10045777

申请日：2002-01-11

Inventor： Tony L. Talbert ,  John Mark Kulo

IPC: B64C013/00

CPC classification number: B64C13/50 ,  B64C31/036 ,  B64C39/024 ,  B64C2201/044 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/123 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64D47/08

Abstract: A remote-control powered parafoil aircraft has an aircraft body (1) that is engine powered and hung with lines (2) from an air-expandable wing (3, 30). The lines include control lines (15) with which air flow and aerodynamic shape of the air-expandable wing are variable selectively from a foil controller (18, 19, 20) on the aircraft body for flight-mode control. Sight from a television camera (8) on the aircraft body is televised to a control unit (9) from which control data is transmitted selectively from proximate the control unit to the foil controller (14) with a multi-axis joystick or similar control, to an engine (6) on the parafoil body from an engine controller (24) and to an item servo (29) for control of optional items (45) on the aircraft body.

Abstract translation: 遥控动力的parafoil飞机具有发动机动力并悬挂有来自可膨胀翼（3,30）的线（2）的飞机主体（1）。 这些管线包括控制线（15），空气膨胀翼的空气流动和空气动力学形状可选择性地从飞行器体上的箔控制器（18,19,20）可变地进行飞行模式控制。 来自飞机机体上的电视摄像机（8）的视线被电视传送到控制单元（9），控制数据通过多轴操纵杆或类似的控制从控制单元的附近被选择性地发送到箔片控制器（14） 从发动机控制器（24）到达副翼车体上的发动机（6）和用于控制飞机主体上的可选项（45）的物品伺服（29）。

公开(公告)号：US6142421A

公开(公告)日：2000-11-07

申请号：US231368

申请日：1999-01-13

Applicant: Miles R. Palmer

Inventor： Miles R. Palmer

IPC: B64C39/02 ,  B64D1/22 ,  B64D37/04 ,  B64D37/06 ,  B64D37/12 ,  B64D39/00 ,  F42B15/00 ,  B64C39/00 ,  B64D37/02

CPC classification number: B64D37/12 ,  B64C39/024 ,  B64D1/22 ,  B64D37/04 ,  B64D37/06 ,  B64D39/00 ,  F42B15/00 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/105 ,  B64C2201/121 ,  B64C2201/126 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/205

Abstract: A vehicle refueling system includes an aero vehicle and a fuel bladder system. The fuel bladder system includes a fuel bladder, a pickup loop of a predetermined loop size, a reel mechanism to retract at least one side of the pickup loop to reduce the loop size, a snag sensor to sense when the pickup loop has been hooked by the retractable hook, the snag sensor initiating the reel mechanism, a compass to sense the random orientation of the loop, a radio navigation receiver to sense a location of the loop, and a transmitter to transmit the random orientation and the location. The vehicle includes a fuselage, a retractable hook with a hook sensor to detect when a fuel bladder is hooked and the loop size has been reduced by the reel mechanism, a fuel bladder stowage chamber within the fuselage, a fuel intake tube capable of drawing fuel from the fuel bladder stowed in the stowage chamber, a retraction mechanism to retract the retractable hook, a fuel transfer mechanism to transfer fuel from the fuel bladder into an internal fuel tank, and a fuel bladder discard mechanism to discard the fuel bladder after the fuel has been drawn from the fuel bladder.

Abstract translation: 车辆加油系统包括航空车辆和燃料囊系统。 燃料囊系统包括燃料囊，预定环尺寸的拾取环，卷绕机构，用于缩回拾取环的至少一侧以减小环的尺寸;阻挡传感器，用于感测拾取环何时已被钩住 可伸缩钩，启动卷轴机构的阻塞传感器，用于感测环路的随机取向的罗盘，用于感测回路位置的无线电导航接收器，以及发送器，以发送随机取向和位置。 车辆包括机身，具有钩传感器的可伸缩钩，用于检测燃料囊何时被钩住，并且通过卷轴机构减小了环路尺寸，机身内部的燃料囊存放室，能够吸引燃料的燃料进入管 从装载在储存室中的燃料气囊，收回缩回钩的缩回机构，用于将燃料从燃料气囊输送到内部燃料箱中的燃料转移机构，以及在燃料之后废弃燃料气囊的燃料气体排出机构 已从燃油囊中抽出。

公开(公告)号：US5340279A

公开(公告)日：1994-08-23

申请号：US903063

申请日：1992-06-22

Applicant: James P. Cycon ,  David H. Hunter ,  Timothy A. Krauss

Inventor： James P. Cycon ,  David H. Hunter ,  Timothy A. Krauss

IPC: B64C27/10 ,  B64C27/20 ,  B64C27/33 ,  B64C27/605 ,  B64C29/00 ,  B64C39/02 ,  B64C39/06 ,  F02B75/02 ,  B64C27/38

CPC classification number: B64C27/20 ,  B64C27/33 ,  B64C27/605 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  F02B2075/025

Abstract: A snubber assembly for a rotor assembly having ducted, coaxial counter-rotating rotors that is design optimized to facilitate utilization of a self-aligning bearing and for installation inboard of the corresponding flexbeam-to-rotor hub attachment joint, thereby enhancing accessibility and reducing maintenance costs. The rotor hub of the rotor assembly is design optimized for securing the snubber assembly in combination therewith and includes a plurality of arms, each arm forming an outboard clevis for attaching the rotor assembly flexbeam to the rotor hub. Inboard of the clevis, each rotor hub arm includes an outboard internal bulkhead having a bolt hole therethrough and an inboard internal bulkhead having a bolt hole therethrough. The inboard and outboard internal bulkheads in combination define a bearing cavity and an internal cavity for securing the snubber assembly in combination with the rotor hub. The snubber assembly includes a spherical self-aligning bearing, a bearing bolt, a locking nut, a snubber bracket secured in combination with the spherical bearing, and securing bolts. The spherical bearing, snubber bracket combination is rotatably mounted within the bearing cavity utilizing the bearing bolt. The bearing bolt is secured in combination with the rotor hub utilizing the locking nut, which is threaded onto the bearing bolt in the internal cavity to jam against the inboard internal bulkhead. The securing bolts are utilized to secure the snubber bracket in combination with the corresponding integrated torque tube/spar member of the rotor assembly.

Abstract translation: 一种用于转子组件的缓冲组件，其具有导管同轴的反向旋转转子，其设计优化以便于利用自对准轴承并安装在对应的挠性梁至转子轮毂附接接头的内侧，从而增强可接近性并减少维护 费用 转子组件的转子轮毂被设计为优化用于将缓冲器组件与其组合固定并且包括多个臂，每个臂形成用于将转子组件挠性束附接到转子毂的外侧U形夹。 在U形夹的内侧，每个转子轮毂臂包括具有穿过其中的螺栓孔的外侧内部隔板和具有穿过其中的螺栓孔的内侧内部隔板。 内侧和外侧的内部舱壁组合地限定了轴承腔和用于将缓冲器组件与转子毂组合固定的内部空腔。 缓冲组件包括球形自调心轴承，轴承螺栓，锁紧螺母，与球面轴承组合固定的缓冲支架和固定螺栓。 球轴承，缓冲支架组合使用轴承螺栓可旋转地安装在轴承腔内。 轴承螺栓利用锁定螺母与转子毂组合固定，该锁定螺母被拧到内部空腔中的轴承螺栓上以卡在内侧内部舱壁上。 紧固螺栓用于将缓冲支架与转子组件的相应的集成扭矩管/翼梁构件组合固定。