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62 条记录 (耗时 0.016 秒)

    SHAPE-CHANGE MATERIAL AND METHOD FOR HEATING THE SAME
    52.
    发明公开
    SHAPE-CHANGE MATERIAL AND METHOD FOR HEATING THE SAME 有权
    格式转换材料与方法加热

    公开(公告)号：EP2411673A1

    公开(公告)日：2012-02-01

    申请号：EP09802074.6

    申请日：2009-12-18

    申请人： Raytheon Company

    发明人： SANDERSON, Terry, M.

    IPC分类号： F03G7/06 ,  B64C3/38 ,  B29C61/06

    CPC分类号： B64C3/54 ,  B29C61/0625 ,  B29L2031/3085 ,  B64C3/26 ,  Y10T428/249953 ,  Y10T428/263

    摘要： A shape-change material includes a shape memory material layer (12) with an electrically conductive layer (14) on a surface of the shape memory material layer. The conductive material may be used to heat the shape memory material by electrical resistance heating. The conductive material (14) may be a primary heater, providing the heating to cause softening or shape change in the shape memory material (12), or may be a secondary heater in conjunction with a greater amount of heating from a primary heater, such as a conductive plate that provides electrical resistance heating to a surface of the shape memory material on an opposite side of the shape memory material (12) from the conductive material (14). One use for the shape-change material is as the skin material for a shape changing material.

    SHAPE-CHANGING STRUCTURE WITH SUPERELASTIC FOAM MATERIAL
    53.
    发明公开
    SHAPE-CHANGING STRUCTURE WITH SUPERELASTIC FOAM MATERIAL 有权
    FORM结构变化超弹性泡沫材料

    公开(公告)号：EP2296963A1

    公开(公告)日：2011-03-23

    申请号：EP09747105.6

    申请日：2009-04-16

    申请人： Raytheon Company

    发明人： SAR, David, R. ,  SANDERSON, Terry, M.

    IPC分类号： B64C3/54 ,  B64C5/02 ,  B64C5/18 ,  F02C7/042 ,  C22F1/18

    CPC分类号： B64C3/54 ,  B64C3/40 ,  B64C5/02 ,  B64C5/18 ,  C22F1/006 ,  C22F1/10 ,  Y02T50/14 ,  Y10T428/12326 ,  Y10T428/12479

    摘要： A shape-changing structure has a superelastic metal foam structural member that changes shape (morphs) to change configuration of the structure. The superelastic metal foam structural member changes shape while maintaining a continuous outer surface, with the continuous metal foam material inside the outer surface expanding, contracting, or otherwise changing shape. The superelastic metal foam material may be heated above a transition temperature to allow it to change shape, and then cooled to cause it to increase in strength, more easily maintaining its new shape. The superelastic metal foam material may be a suitable alloy, for example a nickel titanium alloy, that exhibits superelastic (pseudoelastic) behavior. The superelastic metal foam material may be a shape memory alloy material that returns to a set shape upon moderate heating. The superelastic metal elastic foam structural member may be heated either by an internal heat source or by external heating.

    Ducted fan air vehicle with deployable wings
    54.
    发明公开
    Ducted fan air vehicle with deployable wings 审中-公开
    涵道风扇飞行器与伸缩翼

    公开(公告)号：EP1988014A3

    公开(公告)日：2010-12-08

    申请号：EP08155550.0

    申请日：2008-05-01

    申请人： Honeywell International Inc.

    发明人： Colclough, John C.

    IPC分类号： B64C3/54 ,  B64C27/20 ,  B64C29/02 ,  B64C39/02

    CPC分类号： B64C3/54 ,  B64C27/20 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/162 ,  Y02T50/14

    摘要： A ducted fan air vehicle and method of operation is disclosed for obtaining aerodynamic lift and efficiency in forward fliglit operation without significantly impacting hover stability. One or more retractable wings (301) are included on the ducted fan air vehicle and are deployed during forward flight to provide aerodynamic lift. The wing or wings are retracted when the vehicle hovers to reduce the impact the wings have on stability in a wind. Each wing may conform to the curvature or profile of the vehicle when retracted, and may be constructed in one or more wing sections. The wing or wings may be deployed and retracted automatically or at the command of an operator. Each wing and related components may be integrated into the vehicle or may be detachable.

    Ducted fan air vehicle with deployable wings
    55.
    发明公开
    Ducted fan air vehicle with deployable wings 审中-公开
    Mantelgebläse-Luftfahrzeug mit ausfahrbarenFlügeln

    公开(公告)号：EP1988014A2

    公开(公告)日：2008-11-05

    申请号：EP08155550.0

    申请日：2008-05-01

    申请人： Honeywell International Inc.

    发明人： Colclough, John C.

    IPC分类号： B64C3/54 ,  B64C27/20 ,  B64C29/02 ,  B64C39/02

    CPC分类号： B64C3/54 ,  B64C27/20 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/162 ,  Y02T50/14

    摘要： A ducted fan air vehicle and method of operation is disclosed for obtaining aerodynamic lift and efficiency in forward fliglit operation without significantly impacting hover stability. One or more retractable wings (301) are included on the ducted fan air vehicle and are deployed during forward flight to provide aerodynamic lift. The wing or wings are retracted when the vehicle hovers to reduce the impact the wings have on stability in a wind. Each wing may conform to the curvature or profile of the vehicle when retracted, and may be constructed in one or more wing sections. The wing or wings may be deployed and retracted automatically or at the command of an operator. Each wing and related components may be integrated into the vehicle or may be detachable.

    摘要翻译： 公开了一种管道式风扇空气动力车辆和操作方法，用于获得空气动力提升和前进光束操作的效率，而不会显着影响悬停稳定性。 一个或多个伸缩翼（301）被包括在管道式风扇空气车辆上，并且在向前飞行期间展开以提供空气动力提升。 当车辆悬停时，翼或翼缩回，以减少机翼对风中稳定性的影响。 每个翼可以在缩回时符合车辆的曲率或轮廓，并且可以构造在一个或多个翼部中。 机翼或机翼可以自动或根据操作员的指令进行展开和撤回。 每个翼和相关部件可以集成到车辆中或者可以是可拆卸的。

    EXTENDABLE/RETRACTABLE AIRFOIL ASSEMBLY FOR FIXED WING AIRCRAFT
    57.
    发明授权
    EXTENDABLE/RETRACTABLE AIRFOIL ASSEMBLY FOR FIXED WING AIRCRAFT 失效
    部署/伸缩翼刚性翼飞行设备

    公开(公告)号：EP0973676B1

    公开(公告)日：2005-06-29

    申请号：EP98919740.5

    申请日：1998-04-08

    申请人： Wagner, Fred A., III

    发明人： Wagner, Fred A., III

    IPC分类号： B64C3/54

    CPC分类号： B64C3/54 ,  Y02T50/14

    摘要： A retractable airfoil assembly (20) augments the wing surface area (28) of an aircraft (22) enabling it to fly without stalling at reduced speeds during takeoff and landing. The airfoil assembly includes flexible sails (42, 44) and a furling mast (24) for extending and retracting the sails. The furling mast includes a furling drum mounted for clockwise and counterclockwise rotation on a static tube (50). The flexible sail assembly also includes guide tracks (80) located along a leading edge (101) or tailing edge (40) of the wings. The tracks guide the flexible sails during extension and retraction. A drive cable (26) extends and retracts the sails (42, 44) along the guide tracks and maintains tension in the sails while they are extended.

    An aircraft wing structure and a method for decreasing flight speed of the aircraft
    58.
    发明公开
    An aircraft wing structure and a method for decreasing flight speed of the aircraft 有权
    Flugzeugflügelund Verfahren zur Verringerung der Fluggeschwindigkeit eines Flugzeugs

    公开(公告)号：EP1538075A1

    公开(公告)日：2005-06-08

    申请号：EP04028434.1

    申请日：2004-12-01

    申请人： Top I Vision Ltd.

    发明人： Shental, Gad ,  Shental, Ran ,  Shental, Nir ,  Pessachis, Lev

    IPC分类号： B64C9/32

    CPC分类号： B64C9/02 ,  B64C3/50 ,  B64C3/54 ,  B64C9/18 ,  B64C9/32 ,  B64C9/323

    摘要： The invention provides a wing structure for an aircraft, including a top skin (14) and a bottom skin (16) defining a primary wing surface, the surface having a width, a length, a leading edge (8) and a trailing edge (10); a flap (18) having a width smaller than the width of the wing surface and a length extending over a major portion of the wing length, the flap being hingedly joined adjacent to the trailing edge (10) of the wing, wherein the flap is capable of assuming two limit dispositions, a first disposition in which the flap extends substantially parallel to the bottom skin (16), and a second disposition extending towards the trailing edge (10) of the wing, at an obtuse angle. A method for slowing down the speed of flight of an aircraft is also provided.

    摘要翻译： 本发明提供了一种用于飞行器的机翼结构，其包括限定主翼面的顶部皮肤（14）和底部皮肤（16），所述表面具有宽度，长度，前缘（8）和后缘 10）; 具有小于所述机翼表面的宽度的宽度的翼片（18）以及在所述机翼长度的主要部分上延伸的长度，所述翼片邻近所述机翼的后缘（10）铰接接合，其中所述翼片 能够假设两个极限位置，其中翼片基本上平行于底部皮肤（16）延伸的第一布置，以及以钝角朝向机翼的后缘（10）延伸的第二布置。 还提供了一种降低飞机飞行速度的方法。