中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

6 records (took 0.006 seconds)

    APPARATUS AND METHODS FOR ACTUATION OF FLIGHT CONTROL SURFACES
    1.
    发明申请
    APPARATUS AND METHODS FOR ACTUATION OF FLIGHT CONTROL SURFACES 审中-公开
    用于执行飞行控制表面的装置和方法

    公开(公告)号：WO2015114586A1

    公开(公告)日：2015-08-06

    申请号：PCT/IB2015/050728

    申请日：2015-01-30

    Applicant: BOMBARDIER INC. ,  UNIVERSITÉ DE SHERBROOKE ,  SHORT BROTHERS PLC

    Inventor： NFONGUEM, Gustave ,  CHOUINARD, Patrick ,  PLANTE, Jean - Sebastien

    IPC: B64C13/28

    CPC classification number: B64C13/36 ,  B64C13/28 ,  B64C13/34 ,  F16D37/008 ,  F16D37/02 ,  F16D2023/123 ,  F16D2037/004 ,  F16H1/222

    Abstract: Apparatus and methods for actuating flight control surfaces (16A-C) of fixed-wing aircraft are disclosed herein. An exemplary apparatus disclosed includes a common movable driving member (20) for actuating a plurality of flight control surfaces; a first power transfer device (24A) configured to variably adjust power transfer from the common movable driving member to a first of the plurality of flight control surfaces; and a second power transfer device (24B) configured to variably adjust power transfer from the common movable driving member to a second of the plurality of flight control surfaces. The power transferred to the second flight control surface may be adjusted independently of the power transferred to the first flight control surface. Apparatus and methods for actuating flight control surfaces using magneto-rheological fluid or electro-rheological fluid are also disclosed.

    Abstract translation: 本文公开了用于致动固定翼飞行器的飞行控制表面（16A-C）的装置和方法。 所公开的示例性装置包括用于致动多个飞行控制表面的公共可动驱动构件（20） 第一动力传递装置（24A），其构造成可变地调节从公共可动驱动构件到多个飞行控制表面中的第一个的动力传递; 以及第二动力传递装置（24B），其构造成可变地调节从公共可移动驱动构件到多个飞行控制表面中的第二个的动力传递。 可以独立于传送到第一飞行控制表面的功率来调节传送到第二飞行控制表面的动力。 还公开了使用磁流变流体或电流变流体来致动飞行控制表面的装置和方法。

    HINGE LINE FLIGHT ACTUATOR
    2.
    发明申请
    HINGE LINE FLIGHT ACTUATOR 审中-公开
    铰链飞行执行器

    公开(公告)号：WO1988002720A1

    公开(公告)日：1988-04-21

    申请号：PCT/US1987002704

    申请日：1987-10-19

    Applicant: WEYER, Paul, P.

    IPC: B64C13/36

    CPC classification number: F15B15/068 ,  B64C13/36 ,  F16H25/2204 ,  Y10T74/18888 ,  Y10T74/1896 ,  Y10T74/19767

    Abstract: A fluid-powered rotary actuator (10) for use in operating a aircraft flight control surface, the body (22) of which is comprised of an elongated stationary first end (34) and a rotatable second portion (36), with an elongated annular sleeve (58) reciprocally and coaxially mounted within the body (22). A tie-rod is disposed within the annular sleeve (58) to prevent axial separation of the body portions (34, 36) during actuation. The axially outward portions of the sleeve (58) and the corresponding portions of the stationary and rotatable body portions (34, 36) have helical ball races (108) formed therein to transmit torque between the body portions (34, 36) and the sleeve (58), to cause the rotatable body portion (36) to rotate in response to fluid-powered linear reciprocation of the sleeve (58). The sleeve (58) further contains six recirculation ball races (126) to form six endless ball circuits therein.

    항공기의 비행조종면 구동장치
    4.
    发明申请
    항공기의 비행조종면 구동장치 审中-公开
    飞机飞行控制面驱动装置

    公开(公告)号：WO2012099300A1

    公开(公告)日：2012-07-26

    申请号：PCT/KR2011/003261

    申请日：2011-05-02

    Applicant: 주식회사 한화 ,  윤기준 ,  김상석 ,  박창용 ,  김대현 ,  김상범 ,  장기원 ,  이성택

    Inventor： 윤기준 ,  김상석 ,  박창용 ,  김대현 ,  김상범 ,  장기원 ,  이성택

    IPC: B64C13/28 ,  B64C13/36

    CPC classification number: B64C9/02 ,  B64C13/36 ,  Y02T50/44

    Abstract: 본 발명은 항공기의 비행조종면 구동장치에 관한 것으로 날개 프레임에 액츄에이터가 설치되고 상기 액츄에이터에 의해 전달되는 동력이 비행조종면을 구동하는 항공기의 비행조종면 구동장치에 있어서, 상기 액츄에이터를 상기 날개 프레임에 대해 눕혀지는 방향으로 날개 프레임의 외부에 설치하고, 상기 액츄에이터에서 발생하는 동력을 방향전환수단을 통해 상기 날개 프레임에 대해 세워지는 방향으로 전환시켜 상기 비행조종면에 전달하는 구조로 된 것이다. 본 발명은 날개 프레임에 형성되는 연료저장공간을 효율적으로 활용하고 기체의 중량을 절감할 수 있다는 효과가 있다.

    Abstract translation: 本发明涉及一种飞行器的飞行控制表面驱动装置，其中致动器安装在翼架上，并且由所述致动器传递的动力驱动飞行控制表面，其中本发明构造成使得：所述致动器被安装 在翼架的外侧沿着被放置在所述翼架上的方向; 并且从所述致动器产生的动力通过方向转换装置沿致动器竖立在所述翼架上的方向转换，由此将动力输送到所述飞行控制表面。 本发明有效地利用形成在机翼框架中的燃料存储空间，并且降低了气体的重量。

    APPARATUS AND METHOD FOR HIGH ENERGY DENSITY LINEAR ACTUATION WITH INTEGRAL BRAKING
    5.
    发明申请
    APPARATUS AND METHOD FOR HIGH ENERGY DENSITY LINEAR ACTUATION WITH INTEGRAL BRAKING 审中-公开
    具有整体制动的高能量密度线性致动装置和方法

    公开(公告)号：WO2017007524A1

    公开(公告)日：2017-01-12

    申请号：PCT/US2016/027530

    申请日：2016-04-14

    Applicant: RAYTHEON COMPANY

    Inventor： STAGGERS, David D.

    IPC: F15B15/10 ,  B64C13/36 ,  F42B10/64

    CPC classification number: F15B15/103 ,  B64C13/36 ,  F15B15/19 ,  F15B2211/715 ,  F15B2211/853 ,  F15B2211/8606 ,  F42B10/64

    Abstract: A pneumatic artificial muscle (PAM) actuator (100) includes first and second end caps (102-104), an elastic bladder (106) connected to the end caps, and a covering (108) around the elastic bladder and connected to the end caps. At least one of the first and second end caps is configured to move and narrow a distance between the end caps in response to inflation of the elastic bladder by a fluid. At least one of the end caps includes a vent (114) configured to allow the fluid to exit the elastic bladder and collapse the covering after activation of the PAM actuator. At least the covering is configured to provide braking for the PAM actuator. The covering may be configured to collapse at least partially between the first and second end caps to provide at least some of the braking for the PAM actuator.

    Abstract translation: 气动人造肌肉（PAM）致动器（100）包括第一和第二端盖（102-104），连接到端盖的弹性囊（106）和围绕弹性囊并且连接到端部 帽。 第一和第二端盖中的至少一个被配置成响应于弹性囊由流体膨胀而移动并缩小端盖之间的距离。 端盖中的至少一个包括通气口（114），其配置成允许流体在PAM致动器启动之后离开弹性囊并使覆盖物折叠。 至少覆盖物构造成为PAM致动器提供制动。 覆盖物可以被配置为至少部分地在第一和第二端盖之间折叠以提供用于PAM致动器的至少一些制动。

Patent Agency Ranking