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    TORQUE TUBE DOOR
    2.
    发明申请
    TORQUE TUBE DOOR 有权
    扭矩管门

    公开(公告)号：US20160059952A1

    公开(公告)日：2016-03-03

    申请号：US14469543

    申请日：2014-08-26

    申请人： The Boeing Company

    发明人： Mark Bleazard

    IPC分类号： B64C9/36 ,  B64C9/18

    CPC分类号： B64C9/36 ,  B64C7/00 ,  B64C9/16 ,  B64C9/18

    摘要： A torque tube door and related method steps may include a door coupled to an inboard wing flap, such that the door is movable with the flap to selectively cover and uncover a torque tube opening in an aircraft fuselage.

    摘要翻译： 扭矩管门和相关的方法步骤可以包括联接到内侧翼片的门，使得门能够与挡板一起移动以选择性地覆盖和露出飞机机身中的扭矩管开口。

    AERODYNAMIC BRAKING DEVICE FOR AIRCRAFT
    4.
    发明申请
    AERODYNAMIC BRAKING DEVICE FOR AIRCRAFT 有权
    用于航空器的航空制动装置（AERODYNAMIC BRAKING DEVICE FOR AIRCRAFT）

    公开(公告)号：US20090242698A1

    公开(公告)日：2009-10-01

    申请号：US12415088

    申请日：2009-03-31

    申请人： Hiroki Oyama

    发明人： Hiroki Oyama

    IPC分类号： B64C9/32

    CPC分类号： B64C9/326 ,  B64C9/36 ,  Y02T50/44

    摘要： A speed brake apparatus reduces the airspeed of an aircraft by increasing aerodynamic drag. First and second brake panels are located on opposite sides of a portion of the aircraft, such as the fuselage, and are adapted to swing outward about a downstream hinge axis into deployed positions extending into the air stream. The panels are controlled by an operating device that includes a linear actuator. The actuator moves an operating head connected to a pair of toggle assemblies to convert linear movement of the operating head to the deployment and retraction movement of the brake panels.

    摘要翻译： 速度制动装置通过增加空气动力学阻力来降低飞行器的空速。 第一和第二制动面板位于飞机的诸如机身的一部分的相对侧上，并且适于围绕下游铰链轴向外摆动到延伸到空气流中的展开位置。 面板由包括线性致动器的操作装置控制。 致动器移动连接到一对肘节组件的操作头，以将操作头的线性运动转换成制动面板的展开和缩回运动。

    Wing employing leading edge flaps and winglets to achieve improved aerodynamic performance
    5.
    发明申请
    Wing employing leading edge flaps and winglets to achieve improved aerodynamic performance 审中-公开
    翼采用前缘翼和小翼来实现改善的空气动力学性能

    公开(公告)号：US20050116116A1

    公开(公告)日：2005-06-02

    申请号：US10706671

    申请日：2003-11-11

    申请人： John Morgenstern

    发明人： John Morgenstern

    IPC分类号： B64C3/16 ,  B64C5/02 ,  B64C5/04 ,  B64C5/12 ,  B64C7/00 ,  B64C9/22 ,  B64C9/32 ,  B64C9/36 ,  B64C13/50 ,  B64C23/04 ,  B64C30/00 ,  B64C39/12 ,  B64C3/50

    CPC分类号： B64C39/12 ,  B64C3/16 ,  B64C5/02 ,  B64C5/04 ,  B64C5/12 ,  B64C7/00 ,  B64C9/22 ,  B64C9/32 ,  B64C9/323 ,  B64C9/36 ,  B64C23/04 ,  B64C30/00 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44

    摘要： A wing for use on a supersonic aircraft that includes an inboard section a central section of the wing outboard of the inboard portion, and an outboard section. The outboard section can be a winglet oriented anhedrally relative to a lateral axis of the supersonic aircraft. Leading edge segments on the inboard section, central section and outboard winglet may have mounted thereon leading-edge flaps. These flaps are adjusted by a control system operable to reposition the leading-edge flaps in order to improve the aerodynamic performance of the supersonic aircraft. This winglet promotes sonic boom minimization. Further, the wing tip anhedral allows greater inboard dihedral. This effectively pushes lift aft for sonic boom and control purposes while minimizing the movement of control surfaces.

    摘要翻译： 在超音速飞机上使用的机翼，其包括内侧部分的内侧部分，内侧部分的翼外侧的中心部分和外侧部分。 外侧部分可以是相对于超音速飞行器的横向轴线定向的小翼。 内侧部分，中央部分和外侧小翼上的前缘部分可以安装在前缘翼片上。 这些翼片通过可操作以重新定位前缘翼片的控制系统来调节，以便改善超音速飞机的空气动力学性能。 这个小翼促进了声波的最小化。 此外，翼尖侧面可以更大的内侧二面体。 这样可以有效地将升降机推向震动和控制目的，同时最小化控制面的移动。

    Ducted fan gas turbine engine with surge controller
    6.
    发明授权
    Ducted fan gas turbine engine with surge controller 失效
    带浪涌控制器的风机燃气涡轮发动机

    公开(公告)号：US4930307A

    公开(公告)日：1990-06-05

    申请号：US278445

    申请日：1988-12-01

    申请人： Arnold C. Newton

    发明人： Arnold C. Newton

    IPC分类号： B64C7/02 ,  B64C9/36 ,  F02K1/72 ,  F04D27/02

    CPC分类号： F02K1/72 ,  B64C7/02 ,  B64C9/36 ,  F04D27/002

    摘要： A ducted fan gas turbine engine includes for surge control capability in the form of a downstream fan cowl portion which can be moved to open a gap of variable magnitude. Fixed cowl portion has a resilient downstream edge which effects a good seal against blocker flaps when not in use. The blocker flaps are moved across the fan duct on the cowl portion moving a sufficient distance in a downstream direction.

    摘要翻译： 管式风机燃气涡轮发动机包括用于下游风扇整流罩部分形式的喘振控制能力，该下游风扇整流罩部分可移动以打开可变大小的间隙。 固定整流罩部分具有弹性下游边缘，在不使用时对阻挡片进行良好的密封。 挡板襟翼在整流罩部分的风扇导管上移动，沿下游方向移动足够的距离。

    Shape memory alloy micro-aero control surfaces
    9.
    发明授权
    Shape memory alloy micro-aero control surfaces 有权

    公开(公告)号：US09879959B2

    公开(公告)日：2018-01-30

    申请号：US14057876

    申请日：2013-10-18

    申请人： Raytheon Company

    发明人： Ward D. Lyman ,  Frederick B. Koehler ,  Terry M. Sanderson

    IPC分类号： F42B15/01 ,  F42B10/64 ,  F42B10/62 ,  B64C9/36

    CPC分类号： F42B10/64 ,  B64C9/36 ,  F42B10/62

    摘要： A control system for a missile includes a plurality of control surfaces that can be arrayed across a surface of the missile body, and a controller connected to the control surfaces to selectively move the control surfaces between an aerodynamic stowed position where the control surfaces conform to the surface of the body, and a deployed control position removed from the aerodynamic stowed position where the control surfaces extend from the surface of the body to interact with airflow over the body. The control surfaces are made of a material that includes a shape-memory alloy. Heating the control surfaces causes the shape-memory alloy to move the control surfaces from the aerodynamic stowed position to the deployed control position. By selectively extending and retracting the control surfaces, the control system provides the ability to control the missile's direction of travel or to reduce roll about a longitudinal axis of the body.