公开(公告)号：US20100012790A1

公开(公告)日：2010-01-21

申请号：US12426162

申请日：2009-04-17

Applicant: Nicolae Bostan

Inventor： Nicolae Bostan

IPC: B64C29/04

CPC classification number: B64C3/385 ,  B64C17/06 ,  B64C27/20 ,  B64C29/0033 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165 ,  Y02T50/14

Abstract: A vertical takeoff and landing (VTOL) air vehicle disclosed. The air vehicle can be manned or unmanned. In one embodiment, the air vehicle includes two shrouded propellers, a fuselage and a gyroscopic stabilization disk installed in the fuselage. The gyroscopic stabilization disk can be configured to provide sufficient angular momentum, by sufficient mass and/or sufficient angular velocity, such that the air vehicle is gyroscopically stabilized during various phases of flight. In one embodiment the fuselage is fixedly attached to the shrouded propellers. In another embodiment, the shrouded propellers are pivotably mounted to the fuselage.

Abstract translation: 一架垂直起降（VTOL）的空中客车。 机动车可以载人或无人驾驶。 在一个实施例中，空中交通工具包括安装在机身中的两个被覆盖的螺旋桨，机身和陀螺仪稳定盘。 陀螺稳定盘可以被配置成通过足够的质量和/或足够的角速度来提供足够的角动量，使得在飞行的各个阶段期间航空器的陀螺仪稳定。 在一个实施例中，机身固定地附接到被覆盖的螺旋桨。 在另一个实施例中，被覆盖的螺旋桨可枢转地安装在机身上。

公开(公告)号：US20090283629A1

公开(公告)日：2009-11-19

申请号：US12465912

申请日：2009-05-14

Applicant: David KROETSCH ,  Mike PEASGOOD ,  Dale BRUBACHER-CRESSMAN ,  Cristian CHERLER ,  Stephen MARCHETTI

Inventor： David KROETSCH ,  Mike PEASGOOD ,  Dale BRUBACHER-CRESSMAN ,  Cristian CHERLER ,  Stephen MARCHETTI

IPC: B64C27/08

CPC classification number: B64C39/024 ,  A63H27/12 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108

Abstract: The invention provides a hovering aerial vehicle with removable rotor arms and protective shrouds. Removing the shrouds reduces the weight of the vehicle and increases flight time. Removing the rotor arms makes the vehicle easier to transport. Removable rotor arms also simplify field repair or replacement of damaged parts.

Abstract translation: 本发明提供了具有可拆卸转子臂和保护罩的悬停式飞行器。 卸下护罩减轻了车辆的重量并增加了飞行时间。 拆下转子臂使车辆更容易运输。 可拆卸转子臂还简化了现场维修或更换损坏的零件。

公开(公告)号：US20080223994A1

公开(公告)日：2008-09-18

申请号：US12045207

申请日：2008-03-10

Applicant: Peter Greenley

Inventor： Peter Greenley

IPC: B64C39/00

CPC classification number: A63H27/02 ,  A63H30/04 ,  B64C2201/088

Abstract: The present invention includes an embodiment defined as a flying vehicle having a pair of wings and a transition assembly partially housed within each of the pair of wings. The transition assembly has ends rotatable with respect to each other and separately secured to the wing in which the end is housed. The transition assembly has a first position defined as having each wing positioned at an angle offset from a substantial horizontal orientation and oriented in an opposite direction from the other wing. When the transition assembly is in the first position the vehicle spins and will fly in a substantially hovering vertical orientation. The transition assembly has a second position defined as having each wing positioned in a substantial horizontal position. When the transition assembly is in the second position the vehicle will fly in a substantially horizontal orientation.

Abstract translation: 本发明包括被定义为具有一对翼的飞行器的实施例和部分地容纳在所述一对翼中的每一翼内的过渡组件。 过渡组件具有相对于彼此可旋转的端部，并且单独地固定到其中容纳端部的翼部。 过渡组件具有第一位置，该第一位置被定义为使每个翼定位成与实质水平取向偏移的角度并且朝向与另一翼相反的方向定向。 当过渡组件处于第一位置时，车辆旋转并将以大致悬停的垂直方向飞行。 过渡组件具有第二位置，该第二位置被定义为使每个翼位于基本水平位置。 当过渡组件处于第二位置时，车辆将以基本上水平的方向飞行。

公开(公告)号：US07357352B2

公开(公告)日：2008-04-15

申请号：US11270342

申请日：2005-11-09

Applicant: Thomas E. Speer ,  Richard D. Jones

Inventor： Thomas E. Speer ,  Richard D. Jones

IPC: B64C37/02 ,  B64D5/00

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/162 ,  B64C2201/165 ,  B64D5/00

Abstract: An air vehicle assembly and a corresponding method for launching an air vehicle assembly are provided, along with corresponding control systems and methods. The air vehicle assembly may include a plurality of air vehicles releasably joined to one another during a portion of the flight, such as during take-off and landing. By being releasably joined to one another, such as during take-off and landing, the air vehicles can rely upon and assist one another during the vertical take-off and landing while being designed to have a greater range and higher endurance following the transition to forward flight, either while remaining coupled to or following separation from the other air vehicles. By taking into account the states of the other air vehicles, the control system and method also permit the air vehicles of an air vehicle assembly to collaborate.

Abstract translation: 提供了一种用于发射空中车辆组件的机动车组件和相应的方法，以及相应的控制系统和方法。 空中车辆组件可以包括在飞行的一部分期间例如在起飞和着陆期间可释放地彼此连接的多个空中飞行器。 通过可释放地彼此接合，例如在起飞和着陆期间，空中车辆可以在垂直起飞和着陆期间依靠和协助彼此，同时被设计成在过渡到 同时保持与其他空中客车分离的距离或距离。 通过考虑其他机动车辆的状态，控制系统和方法还允许机动车组件的空中车辆协作。

公开(公告)号：US20070102565A1

公开(公告)日：2007-05-10

申请号：US11270342

申请日：2005-11-09

Applicant: Thomas Speer ,  Richard Jones

Inventor： Thomas Speer ,  Richard Jones

IPC: B64C29/00 ,  B64C37/02

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/162 ,  B64C2201/165 ,  B64D5/00

Abstract: An air vehicle assembly and a corresponding method for launching an air vehicle assembly are provided, along with corresponding control systems and methods. The air vehicle assembly may include a plurality of air vehicles releasably joined to one another during a portion of the flight, such as during take-off and landing. By being releasably joined to one another, such as during take-off and landing, the air vehicles can rely upon and assist one another during the vertical take-off and landing while being designed to have a greater range and higher endurance following the transition to forward flight, either while remaining coupled to or following separation from the other air vehicles. By taking into account the states of the other air vehicles, the control system and method also permit the air vehicles of an air vehicle assembly to collaborate.

Abstract translation: 提供了一种用于发射空中车辆组件的机动车组件和相应的方法，以及相应的控制系统和方法。 空中车辆组件可以包括在飞行的一部分期间例如在起飞和着陆期间可释放地彼此连接的多个空中飞行器。 通过可释放地彼此接合，例如在起飞和着陆期间，空中车辆可以在垂直起飞和着陆期间依靠和协助彼此，同时被设计成在过渡到 同时保持与其他空中客车分离的距离或距离。 通过考虑其他机动车辆的状态，控制系统和方法还允许机动车组件的空中车辆协作。

公开(公告)号：US20050082422A1

公开(公告)日：2005-04-21

申请号：US10690284

申请日：2003-10-21

Applicant: Glenn Tierney

Inventor： Glenn Tierney

IPC: B64B1/30 ,  B64C39/00 ,  B64C39/02 ,  B64C27/00

CPC classification number: B64C39/005 ,  B64B1/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/165

Abstract: A system and method for moving an aerial vehicle along a flight path includes rotatable hubs mounted on opposite sides of the vehicle. Elongated airfoils are mounted on the hubs parallel to a common hub axis for rotation about the hub axis on a blade path. Each airfoil defines a chord line and the system includes a gear assembly changeable, during hub rotation, between a first modality wherein airfoil chord lines remain tangential to the blade path (curtate flight), and a second modality wherein airfoil chord lines remain parallel to the flight path of the vehicle (prolate flight). Also, rotation of the hub can be stopped and the airfoils used for fixed wing flight.

公开(公告)号：US20040129828A1

公开(公告)日：2004-07-08

申请号：US10390222

申请日：2003-03-17

Inventor： Nicolae Bostan

IPC: B64C015/00 ,  B64C029/00

CPC classification number: B64C17/06 ,  B64C29/0025 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162

Abstract: An unmanned air vehicle comprises a fuselage that defines aerodynamic flight surfaces, an engine mounted to the fuselage having an engine shaft arranged to rotate about a longitudinal axis with respect to the fuselage, and a propeller mounted to the engine shaft so as to rotate to thereby provide thrust. The aircraft also comprises a gyroscopic stabilization member coupled to the shaft such that rotation of the engine shaft results in rotation of the gyroscopic member. Thus, there is more stability during the entire flight envelope. In one embodiment, the gyroscopic stabilization member is comprised of a ring that is attached to the outer ends of the blades of the propeller and the ring is also selected so as to have a mass that will result in the gyroscopic stabilization member having a sufficient angular momentum so as to gyroscopically stabilize the aircraft.

Abstract translation: 无人驾驶飞行器包括限定空气动力学飞行表面的机身，安装到机身上的发动机，其具有被布置为围绕相对于机身的纵向轴线旋转的发动机轴，以及安装到发动机轴上以便旋转的螺旋桨 提供推力。 飞机还包括联接到轴的陀螺稳定构件，使得发动机轴的旋转导致陀螺仪构件的旋转。 因此，在整个飞行包络中有更多的稳定性。 在一个实施例中，陀螺稳定构件包括附接到螺旋桨的叶片的外端的环，并且环也被选择为具有将导致陀螺稳定构件具有足够角度的质量 动力，以便陀螺仪稳定飞机。

公开(公告)号：US20030052222A1

公开(公告)日：2003-03-20

申请号：US10191733

申请日：2002-07-08

Inventor： John M. Plump ,  Neil R. Gupta

IPC: B64C029/00

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C39/062 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/162

Abstract: An aerial vehicle including a toroidal fuselage having a longitudinal axis, and a duct extending along the longitudinal axis between a leading edge and a trailing edge of the fuselage, first and second counter-rotating, variable pitch rotor assemblies coaxially mounted within the duct of the fuselage, and at least one canard wing secured to the toroidal fuselage and having a leading edge positioned out of the duct of the fuselage and axially forward of the leading edge of the fuselage, wherein at least a portion of the canard wing comprises a control surface having a variable angle of attack. The invention provides an aerial vehicle that can take-off and land vertically, hover for extended periods of time over a fixed spatial point, and operate in confined areas. The aerial vehicle also has the ability to transition between a hover and high speed forward flight.

Abstract translation: 一种包括具有纵向轴线的环形机身的航空器以及沿着纵向轴线在机身的前缘和后缘之间延伸的管道，同轴地安装在机身的管道内的第一和第二反向旋转的变桨距转子组件 机身，以及至少一个固定在环形机身上的鸭翼，其前缘位于机身的导管之外并且在机身的前缘的轴向前方，其中，所述鸭翼的至少一部分包括控制表面 具有可变的迎角。 本发明提供一种能够垂直起飞并垂直着陆的飞行器，在固定的空间点上长时间悬停，并在密闭区域内操作。 飞行器还具有在悬停和高速前进飞行之间转换的能力。

公开(公告)号：US06409122B1

公开(公告)日：2002-06-25

申请号：US09761076

申请日：2001-01-17

Applicant: Leland M. Nicolai

Inventor： Leland M. Nicolai

IPC: B64C3500

CPC classification number: B64C35/005 ,  B60V1/08 ,  B64C39/024 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/167 ,  B64C2201/187

Abstract: An anti-submarine warfare system includes an unmanned “sea-sitting” aircraft housing submarine detecting equipment, the aircraft including a body portion having a catamaran configuration adapted for stably supporting the body portion when sitting in water, the body portion including a fuselage and laterally disposed sponsons connected to the fuselage via platforms, and submarine detecting equipment housed within the fuselage and adapted to be electronically linked to sonobuoys disposed in adjacent water locations.

Abstract translation: 一种反潜战系统包括一个无人“海坐”飞机舱潜艇检测设备，该飞机包括一个主体部分，该主体部分具有适于在坐在水中时稳定地支撑主体部分的双体船结构，该主体部分包括机身和横向 通过平台连接到机身的安装支架，以及容纳在机身内的潜艇检测设备，并且适于与设置在相邻水位的声波电子电子连接。

公开(公告)号：US5340057A

公开(公告)日：1994-08-23

申请号：US850913

申请日：1992-03-13

Applicant: Hugh Schmittle

Inventor： Hugh Schmittle

IPC: B64C3/38 ,  B64C29/00 ,  B64C29/02 ,  B64C39/02 ,  B64C39/04

CPC classification number: B64C39/024 ,  B64C29/0033 ,  B64C29/02 ,  B64C3/385 ,  B64C39/04 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64D2201/00

Abstract: The VTOL aircraft includes a free wing having wings on opposite sides of the fuselage connected to one another for joint free rotation and for differential pitch settings under pilot, computer or remote control. On vertical launch, pitch, yaw and roll control is effected by the elevators, rudder and the differential pitch settings of the wings, respectively. At launch, the elevator pitches the fuselage nose downwardly to alter the thrust vector and provide horizontal speed to the aircraft whereby the free wing freely rotates relative to the fuselage into a generally horizontal orientation to provide lift during horizontal flight. Transition from horizontal to vertical flight is achieved by the reverse process and tile aircraft may be gently recovered in or on a resilient surface such as a net.

Abstract translation: 垂直起落架飞机包括一个自由翼，在机身的相对两侧具有彼此连接的翼，用于联合自由旋转，并在飞行员，计算机或遥控器下进行差距俯仰设置。 在垂直发射时，俯仰，偏航和侧倾控制分别由电梯，方向舵和翼的差距俯仰设置来实现。 在发射时，升降机将机身鼻部向下倾斜以改变推力矢量并向飞行器提供水平速度，由此自由翼相对于机身自由旋转成大致水平的方向以在水平飞行期间提供升力。 从水平飞行到垂直飞行的过渡是通过相反的过程实现的，瓦片飞机可以在诸如网络的弹性表面中或其上轻轻地回收。