利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

674 条记录 (耗时 0.021 秒)

    X-wing helicopter-scout attack configuration
    81.
    发明授权
    X-wing helicopter-scout attack configuration 失效
    X翼直升机侦察攻击配置

    公开(公告)号：US4711415A

    公开(公告)日：1987-12-08

    申请号：US696604

    申请日：1985-01-30

    申请人： John A. Binden

    发明人： John A. Binden

    IPC分类号： B64C27/32 ,  B64C27/82

    CPC分类号： B64C27/325 ,  B64C27/82 ,  B64C2027/8245

    摘要： The present invention provides a single seat aircraft having the capabilities of vertical takeoff, landing and hovering operations utilizing the X-Wing as a conventional helicopter rotating wing. After transition to forward flight following takeoff, the rotating wing is stopped and becomes a fixed wing of "X" configuration. The aircraft utilizes two engines within the fuselage, one engine being positioned vertically above the other along the longitudinal axis of the aircraft, the particular arrangement of engines allowing aircraft size and weight to be substantially reduced.

    摘要翻译： 本发明提供一种具有垂直起飞，着陆和悬停操作的能力的单座飞机，其利用X翼作为传统的直升机旋翼。 在起飞后向前飞行过渡后，旋转翼停止，成为“X”构型的固定翼。 飞机在机身内部使用两个发动机，一个发动机沿着飞机的纵向轴线垂直地位于另一个之上，发动机的特定布置允许飞机的尺寸和重量大大减小。

    Tail rotor arrangement with increased thrust for rotary wing aircraft and device for increasing the thrust of such an arrangement
    82.
    发明授权
    Tail rotor arrangement with increased thrust for rotary wing aircraft and device for increasing the thrust of such an arrangement 失效
    尾翼转子布置，其具有用于旋转翼飞机的增加的推力和用于增加这种布置的推力的装置

    公开(公告)号：US4585391A

    公开(公告)日：1986-04-29

    申请号：US536387

    申请日：1983-09-27

    申请人： Alain Vuillet ,  Francoise J. Morelli

    发明人： Alain Vuillet ,  Francoise J. Morelli

    IPC分类号： B64C27/82 ,  B64C27/78 ,  F04D29/44

    CPC分类号： B64C27/82 ,  B64C2027/8254 ,  Y10S415/914

    摘要： A tail rotor arrangement for rotary wing aircraft, comprising a tunnel of axis X--X transverse with respect to the aircraft and in which is disposed a multi-blade rotor coaxial with respect to the tunnel and generating a transverse air flow. The arrangement comprises a plurality of fixed blades disposed inside of the tunnel downstream of the rotor with respect to the air flow and arranged in at least substantially radial manner with respect to the tunnel in order to be able to recover, in the form of an axial thrust, the energy of rotation of the air flow at the outlet of the rotor. The tail rotor arrangement provides an increase in thrust of the rotors, particularly paired rotors.

    摘要翻译： 一种用于旋转翼飞行器的尾部转子装置，包括相对于飞行器横向的X-X轴的隧道，并且其中设置有相对于隧道同轴的多叶片转子并产生横向空气流。 该装置包括多个固定刀片，其设置在转子相对于空气流下游的隧道内部，并且相对于隧道以至少基本上径向的方式布置，以便能够以轴向的形式恢复 推力，转子出口处气流的旋转能量。 尾转子装置提供了转子，特别是配对转子的推力的增加。

    Compound helicopter drive means
    83.
    发明授权
    Compound helicopter drive means 失效
    复合式直升机驱动方式

    公开(公告)号：US3977812A

    公开(公告)日：1976-08-31

    申请号：US632340

    申请日：1975-11-17

    申请人： Wayne A. Hudgins

    发明人： Wayne A. Hudgins

    IPC分类号： B64C27/12 ,  B64C27/82 ,  B64C27/22

    CPC分类号： B64C27/12 ,  B64C27/82 ,  B64C2027/8236

    摘要： Compound helicopters, those having a rotor blade and a small wing, possess rear propulsion propeller adjacent to the tail rotor. The tail gearbox is driven through a drive train coupled to the main rotor drive shaft. In such aircraft the tail rotor is in operation when the propulsion propeller is turning, and vice versa. A mechanism is provided herein for stopping or feathering the tail rotor when driving the propulsion propeller, or for stopping the propulsion propeller when the tail rotor is in operation.

    摘要翻译： 具有转子叶片和小翼的复合直升机具有与尾部转子相邻的后推进推进器。 尾部变速箱通过联接到主转子驱动轴的传动系统驱动。 在这种飞行器中，当推进推进器正在转动时，尾部转子正在运行，反之亦然。 本文提供了一种用于在驱动推进推进器时停止或羽化尾部转子的机构，或者在尾部转子运行时停止推进螺旋桨。

    Flight control system hardover monitor with provisions for preventing nuisance alarms
    84.
    发明授权
    Flight control system hardover monitor with provisions for preventing nuisance alarms 失效
    飞行控制系统硬件监控器，防止误报警

    公开(公告)号：US3880385A

    公开(公告)日：1975-04-29

    申请号：US40191073

    申请日：1973-09-28

    申请人： BENDIX CORP

    发明人： REYNOLDS GIBSON ,  DONIGER JERRY

    IPC分类号： B64C1/00 ,  B64C27/82 ,  G05D1/00 ,  B64C13/18

    CPC分类号： B64C27/82 ,  G05D1/0061

    摘要： A monitor for a flight control system provides an alarm and/or disconnects the system when pitch axis hardover failures occur, whereupon corrective action may be taken to insure flight safety during critical maneuvers. Apparatus is provided for inhibiting the monitor during control wheel steering of the craft and for an out-of-trim condition of the aircraft elevator. The monitoring range is extended by monitoring pitch rate during level turns of the craft.

    摘要翻译： 飞行控制系统的监视器在发生俯仰轴故障发生时提供报警和/或断开系统，因此可能采取纠正措施以确保在重要操作过程中的飞行安全。 提供了用于在飞行器的控制轮转向和用于飞行器升降机的非修剪状态的情况下禁止监视器的装置。 监视范围通过监视船舶水平转弯期间的俯仰速率来延长。

    Redundant stabilizer support
    85.
    发明授权
    Redundant stabilizer support 失效
    冗余稳定器支持

    公开(公告)号：US3706432A

    公开(公告)日：1972-12-19

    申请号：US3706432D

    申请日：1971-09-14

    申请人： UNITED AIRCRAFT CORP

    发明人： ACCASHIAN JOHN

    IPC分类号： B64C27/26 ,  B64C27/82 ,  B64C13/04

    CPC分类号： B64C27/82 ,  B64C2027/8281

    摘要： A horizontal stabilizer for a helicopter has two airfoil sections, one on each side of a tail cone. A stabilizer joining and torque tube mechanism comprising two concentric tubes mounted on bearings in the tail cone extends through the tail cone and beyond into the airfoil sections wherein the tubes terminate at laterally spaced points, the inner tube being longer than the outer tube. To transmit torque from the shafts to the airfoil sections a torque tube housing is provided in each airfoil section which conforms externally to and is connected to its airfoil section and which receives the end portions of both tubes and is bolted to them. An actuating lever for the stabilizer is provided on the torque tube mechanism within the tail cone which is connected to pilot controlled linkage.

    摘要翻译： 用于直升机的水平稳定器具有两个翼型部分，一个在尾锥的每一侧。 稳定器接合和扭矩管机构包括安装在尾锥中的轴承上的两个同心管延伸穿过尾锥并且超过翼型部分，其中管终止在横向间隔的点处，内管比外管长。 为了将扭矩从轴传递到翼型部分，在每个翼型部分设置有扭矩管壳体，其在外部连接到翼型部分并且连接到其翼型部分，并且接收两个管的端部并且螺栓连接到它们。 用于稳定器的致动杆设置在连接到先导控制连杆的尾锥内的扭矩管机构上。