中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

643 records (took 0.021 seconds)

    AIR VEHICLE
    282.
    发明公开
    AIR VEHICLE 有权
    LUFTFAHRZEUG

    公开(公告)号：EP2435306A2

    公开(公告)日：2012-04-04

    申请号：EP10732752.0

    申请日：2010-05-26

    Applicant: Israel Aerospace Industries Ltd.

    Inventor： WOLFF, Amit ,  DEKEL, Guy ,  ZIVAN, Lior

    IPC: B64C29/00

    CPC classification number: B64C29/0033 ,  B64C27/22 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/126 ,  B64C2201/165 ,  B64C2211/00

    Abstract: In embodiments, a system and method for providing propulsion and control to an air vehicle, and for operating the vehicle, include at least three propulsion units that provide vertical thrust for vectored thrust flight, in which at least one or two of the propulsion units also provide thrust for vectored thrust cruising or aerodynamic flight by suitably tilting the respective propulsion units for changing the thrust vector thereof. At the same time, the three or more propulsion units are operated to generate controlling moments to the air vehicle about three orthogonal axes, pitch, roll and yaw, during vectored thrust flight (hover, cruising, etc.) or during aerodynamic flight for controlling the vehicle.

    Abstract translation: 在实施例中，用于向空中交通工具提供推进和控制以及用于操作车辆的系统和方法包括至少三个推进单元，其提供用于向量推力飞行的垂直推力，其中至少一个或两个推进单元也 通过适当地倾斜相应的推进单元来改变其推力矢量，为向量推力巡航或空气动力学飞行提供推力。 同时，三个或更多的推进单元被操作以在向量推力飞行（悬停，巡航等）期间或在用于控制的空气动力学飞行期间在三个正交轴线（俯仰，滚动和偏航）周围产生对空中飞行器的控制力矩 机动车。

    Method and apparatus for automated launch, retrieval, and servicing of a hovering aircraft
    283.
    发明公开
    Method and apparatus for automated launch, retrieval, and servicing of a hovering aircraft 审中-公开
    方法和用于自动启动装置，检索和操纵飞机盘旋

    公开(公告)号：EP2371715A2

    公开(公告)日：2011-10-05

    申请号：EP11159710.0

    申请日：2011-03-25

    Applicant: Aerovel Corporation

    Inventor： McGeer, Brian Theodore ,  Heavey, Robert Joseph ,  McMillan, Damon Lucas ,  Stafford, John William

    IPC: B64F1/02 ,  B64F1/04

    CPC classification number: B64F1/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/182 ,  B64D37/00 ,  B64F5/00

    Abstract: An aircraft capable of thrust-borne flight can be automatically retrieved, serviced, and launched using equipment suitable for use on a small vessel, or at a base with similarly limited space or irregular motion. For retrieval, the aircraft drops a tether, and pulls the tether at low relative speed into contact with a horizontal guide. The tether is pulled across the guide until the guide is captured by a hook or other end effector. The tether length is then adjusted as necessary, and the aircraft swings on the guide to hang in an inverted position. Translation of the tether along the guide then brings the aircraft to a docking carriage, in which the aircraft parks for servicing. For launch the carriage is swung upright, the end effector is released from the guide, and the aircraft thrusts into free flight. A full ground-handling cycle can thus be accomplished automatically with simple and economical apparatus. It can be used with low risk of damage, and requires only moderate accuracy in manual or automatic flight control.

    Abstract translation: 能够推力传飞行的飞机可以被自动检索，维修和使用适合于使用设备上的一个小容器推出，或者在具有类似的限制空间或不规则的运动的位置。 进行检索，飞机下降的系绳，并且拉动在低相对速度系绳与水平引导接触。 直到所述引导件通过钩或其它端部执行器中捕获的系绳横越导拉动。 然后系绳长度被调整为必要的，并且在引导飞机摆动到在倒置位置挂出。 沿导系绳的翻译，那么带来的飞机对接的马车，其中飞机公园进行维修。 对于发射架摆动直立，末端执行器从引导释放，飞机推力到自由飞行。 全地处理周期因此可以提供简单而经济的装置自动完成。 它可以与损坏的风险低一起使用，并且只需要在手动或自动飞行控制中等精度。

    AIRCRAFT
    284.
    发明公开
    AIRCRAFT 有权
    飞机

    公开(公告)号：EP2212199A1

    公开(公告)日：2010-08-04

    申请号：EP08851341.1

    申请日：2008-11-20

    Applicant: QinetiQ Limited

    Inventor： HOTHI, Inderpal, Singh ,  STOACKLEY, Jon, Robert ,  STOACKLEY, Steven, John

    IPC: B64C29/02 ,  B64C39/02

    CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/088

    Abstract: An unmanned aerial vehicle (UAV) (1) in the form of a 'tail sitter' flying wing (1) adapted for vertical take off and landing and transitions between flight as a helicopter and wing-borne flight. The vehicle is electrically powered from onboard batteries and equipped with rotors (7) on miniature helicopter rotor heads (8) at the tips of the wing for both lift, during take off and landing, and forward thrust. In planform the wing (1) comprises, to each side of its longitudinal axis, an inner section (2) with swept back leading and trailing edges, and an outer section (3) with a leading edge more perpendicular to the longitudinal axis, being only mildly swept back or substantially unswept, and a swept forward trailing edge.

    Abstract translation: 无人驾驶飞行器（UAV）（1）采用“尾翼”飞行翼（1）的形式，适用于垂直起飞和降落，以及直升机和机翼飞行之间的飞行过渡。 该车辆由机载电池供电，并且在机翼顶端的微型直升机旋翼头（8）上配备有转子（7），用于升降，起飞和着陆期间以及向前推力。 在平面形式中，机翼（1）在其纵向轴线的每一侧包括具有前后扫掠后缘的内部部分（2）和具有更加垂直于纵向轴线的前缘的外部部分（3）， 只是轻微地扫过或基本没有扫过，并且向前扫过。

    Launch and capture systems for vertical take-off and landing (VTOL) vehicles
    285.
    发明公开
    Launch and capture systems for vertical take-off and landing (VTOL) vehicles 审中-公开
    开始和结束系统启动和登陆Fahrzeug

    公开(公告)号：EP2103518A2

    公开(公告)日：2009-09-23

    申请号：EP09153384.4

    申请日：2009-02-21

    Applicant: Honeywell International Inc.

    Inventor： Goossen, Emray R. ,  Sheoran, Yogendra Y.

    IPC: B64F1/04

    CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/182 ,  B64C2201/201 ,  B64C2201/205 ,  B64C2201/208 ,  B64F1/04

    Abstract: A launch and capture system for capturing a vertical take-off and landing (VTOL) vehicle having a thruster (104) and a duct (106) configured to direct airflow generated by the thruster includes a capture plate (120) and an extension (122). The capture plate is configured to alter the airflow and generate a force attracting the duct to the capture plate. The extension is coupled to the capture plate, and is configured to at least facilitate holding the VTOL vehicle against the capture plate.

    Abstract translation: 用于捕获具有推进器（104）和构造成引导由推进器产生的气流的管道（106）的垂直起飞和着陆（VTOL）车辆的发射和捕获系统包括捕获板（120）和延伸部（122） ）。 捕获板被配置为改变气流并产生吸引到捕获板的管道的力。 延伸部联接到捕获板，并且被构造成至少有利于将VTOL车辆保持抵靠捕获板。

    THRUST VECTORING FREE WING AIRCRAFT
    288.
    发明授权
    THRUST VECTORING FREE WING AIRCRAFT 失效
    带飞翼和推力反向PLANE

    公开(公告)号：EP0629164B1

    公开(公告)日：1999-05-26

    申请号：EP93907455.5

    申请日：1993-03-12

    Applicant: SCHMITTLE, Hugh J.

    Inventor： SCHMITTLE, Hugh J.

    IPC: B64C3/38

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

    Abstract: The VTOL aircraft (10) includes a free wing (16) having wings on opposite sides of the fuselage (12) 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 (26), rudder (24) and the differential pitch settings of the wings, respectively. At launch, the elevator (26) pitches the fuselage (12) nose downwardly to alter the thrust vector and provide horizontal speed to the aircraft whereby the free wing (16) rotates relative to the fuselage (12) into a generally horizontal orientation to provide lift during horizontal flight. Transition from horizontal to vertical flight is achieved by the reverse process and the aircraft may be gently recovered in or on a resilient surface such as a net (66).

Patent Agency Ranking