公开(公告)号：US20080078887A1

公开(公告)日：2008-04-03

申请号：US11531200

申请日：2006-09-12

Applicant: Randy L. Gaigler

Inventor： Randy L. Gaigler

IPC: B64G1/00

CPC classification number: B64G1/641 ,  B64C2201/088 ,  F42B12/58

Abstract: An apparatus that provides shock absorption and ejection for a payload that is to be deployed from a launch capsule is disclosed. The payload ejection mechanism comprises a movable housing that houses a resilient member and a shock-damping system. The rapid acceleration of the capsule upon launch causes the movable housing to move, which compresses the resilient member, thereby storing energy. Movement of the housing also provides shock damping behavior. A locking mechanism maintains the compression of the resilient member until the capsule opens to deploy the payload. As the capsule opens, a restraint decouples from the locking mechanism and permits the resilient member to expand. Expansion of the resilient member causes the movable housing to move, thereby propelling the payload away from the capsule.

Abstract translation: 公开了一种为从发射舱部署的有效载荷提供减震和弹射的装置。 有效载荷弹出机构包括容纳弹性构件和减震系统的可动壳体。 胶囊在发射时的快速加速导致可动壳体移动，从而压缩弹性部件，由此储存能量。 房屋的运动也提供减震行为。 锁定机构保持弹性构件的压缩直到胶囊打开以展开有效载荷。 当胶囊打开时，约束件与锁定机构分离并允许弹性部件膨胀。 弹性构件的膨胀使得可移动壳体移动，从而将有效载荷推离胶囊。

公开(公告)号：US20070034737A1

公开(公告)日：2007-02-15

申请号：US11200319

申请日：2005-08-09

Applicant: Glenn Tierney

Inventor： Glenn Tierney

IPC: B64C39/00

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.

Abstract translation: 沿着飞行路径移动飞行器的系统和方法包括安装在车辆的相对侧上的可旋转轮毂。 细长的翼型件平行于公共轮毂轴线安装在轮毂上，以便在叶片路径上围绕轮毂轴线旋转。 每个翼型件限定弦线，并且该系统包括齿轮组件，在轮毂旋转期间，其中翼型弦线保持与叶片路径相切的第一模态（curtate飞行）和第二模态，其中翼型弦线保持平行于 车辆的飞行路线（长跑）。 此外，轮毂的旋转可以停止，翼型件用于固定翼飞行。

公开(公告)号：US20060278757A1

公开(公告)日：2006-12-14

申请号：US10558312

申请日：2004-05-20

Applicant: Christopher Kelleher

Inventor： Christopher Kelleher

IPC: B64C37/02 ,  B64F1/04

CPC classification number: B64C37/02 ,  B64C39/024 ,  B64C39/026 ,  B64C2201/021 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/101 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/148 ,  B64C2201/201 ,  B64D5/00

Abstract: A heavier-than-air air vehicle, particularly a long endurance, solar powered, unmanned aerial vehicle (UAV) intended for “perpetual” flight within the stratosphere, is carried to its operational altitude suspended on a tether from a helium balloon. The tether is attached at or towards a tip of the UAV's wing so that it is carried in effectively a 90° banked attitude. At the desired altitude the UAV's powerplant is started and it flies on its tether in an upwardly-spiralling path relative to the balloon until a level or near level attitude is attained, when the tether is released and the UAV is permitted to assume free flight.

公开(公告)号：US20060231675A1

公开(公告)日：2006-10-19

申请号：US11384167

申请日：2006-03-17

Applicant: Nicolae Bostan

Inventor： Nicolae Bostan

IPC: B64C29/00

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.

公开(公告)号：US07044422B2

公开(公告)日：2006-05-16

申请号：US10390222

申请日：2003-03-17

Applicant: Nicolae Bostan

Inventor： Nicolae Bostan

IPC: B64C29/00

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：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：US06691949B2

公开(公告)日：2004-02-17

申请号：US10191733

申请日：2002-07-08

Applicant: John M. Plump ,  Neil R. Gupta

Inventor： John M. Plump ,  Neil R. Gupta

IPC: B64C2722

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：US06604706B1

公开(公告)日：2003-08-12

申请号：US09763714

申请日：2001-02-22

Applicant: Nicolae Bostan

Inventor： Nicolae Bostan

IPC: B64C2900

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 (UAV) having a ducted fan configuration with a propeller mounted inside of an opening that extends longitudinally through a fuselage. A gyroscopic stabilization device is attached to the propeller shaft such that rotation of the propeller shaft also results in rotation of the gyroscopic stabilization device. The gyroscopic stabilization device has sufficient mass and rotates at a sufficient angular velocity such that the aircraft is gyroscopically stabilized during flight. In one embodiment, the gyroscopic stabilization device comprises a ring mounted to the outer tips of the propeller and in another embodiment is comprised of a disc.

Abstract translation: 具有风扇构造的无人驾驶飞行器（UAV），其具有安装在通过机身纵向延伸的开口内部的螺旋桨。 陀螺稳定装置连接到传动轴上，使得传动轴的旋转也导致陀螺稳定装置的旋转。 陀螺稳定装置具有足够的质量并以足够的角速度旋转，使得飞行器在飞行期间被陀螺稳定。 在一个实施例中，陀螺稳定装置包括安装到螺旋桨的外部尖端的环，并且在另一个实施例中由圆盘组成。

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：US6086015A

公开(公告)日：2000-07-11

申请号：US307016

申请日：1999-05-07

Applicant: Paul B. MacCready, Jr.

Inventor： Paul B. MacCready, Jr.

IPC: B64C29/02 ,  B64C39/02 ,  B64D1/08 ,  B64D1/22 ,  B64C29/00

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64D1/08 ,  B64D1/22 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/165

Abstract: Apparatus for transporting a load between source and destination locations, comprising an aircraft having a body, power plant carried by the body to drive the aircraft both generally vertically and also generally horizontally, the aircraft also having a wing structure that has a leading edge remaining presented in the direction of flight; and load pick-up, carry and set-down means connected to the aircraft to elevate the load from the source location, transport the elevated and air-borne load generally horizontally, and set the load down at the destination location, the body and power plant configured for vertical flight mode to elevate and set down the load, and for generally horizontal flight mode to transport the elevated load generally horizontally below the level of the aircraft body.

Abstract translation: 用于在源和目的地之间运输负载的装置，包括具有主体的飞行器，由所述主体承载的动力装置，以大致垂直地并且大致水平地驱动飞行器，飞行器还具有保持呈现的前缘的翼结构 在飞行方向; 以及连接到飞机的负载拾取，携带和设置装置，以提高源头的负载，大体上水平地运输高空和空载负载，并将负载设置在目的地，机体和功率 配置用于垂直飞行模式的设备可提升和降低负载，并且大体上为水平飞行模式，以将升高的载荷大致水平地运送到飞机主体的水平面以下。