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    AN AIRCRAFT WITH A STRUT-BRACED FOLDABLE WING
    1.
    发明申请
    AN AIRCRAFT WITH A STRUT-BRACED FOLDABLE WING 审中-公开
    具有可弯曲折边的飞机

    公开(公告)号：WO2015150818A1

    公开(公告)日：2015-10-08

    申请号：PCT/GB2015/051034

    申请日：2015-04-02

    申请人： AIRBUS OPERATIONS LIMTED

    发明人： WRIGHT, Philip

    IPC分类号： B64C3/56

    CPC分类号： B64C3/56 ,  B64D29/02 ,  Y02T50/14

    摘要： An aircraft (1) comprising a wing (5), the wing comprising an inner region (5a) and an outer region (5b), the inner and outer regions (5a, 5b) being connected by a hinge (11) defining a hinge line about which the outer region (5b) is foldable to reduce the span of the wing. The aircraft (1) comprises an actuator (13) arranged to actuate the folding of the outer region (5b) of the wing with an actuation force. The wing (5) is braced by an external strut structure (9) for transferring some of the wing loadings in the outer region (5b) of the wing away from the inner region of the wing (5a). The actuator (13) is arranged to exert the actuation force via the strut structure (9).

    摘要翻译： 1.一种飞机（1），包括翼（5），所述翼包括内部区域（5a）和外部区域（5b），所述内部区域和外部区域（5a，5b）通过铰链（11）连接，所述铰链限定铰链 外部区域（5b）围绕其可折叠以减小翼的跨度。 飞行器（1）包括致动器（13），致动器（13）被布置成用致动力致动翼的外部区域（5b）的折叠。 机翼（5）由外部支柱结构（9）支撑，用于将翼的外部区域（5b）中的一些翼部载荷转移离开翼部（5a）的内部区域。 致动器（13）被布置成经由支柱结构（9）施加致动力。

    SHUTTER MECHANISM FOR COVERING A WING DEPLOYMENT OPENING
    2.
    发明申请
    SHUTTER MECHANISM FOR COVERING A WING DEPLOYMENT OPENING 审中-公开
    用于覆盖部署开放的快门机制

    公开(公告)号：WO2014203237A2

    公开(公告)日：2014-12-24

    申请号：PCT/IL2014/050422

    申请日：2014-05-14

    申请人： RAFAEL ADVANCED DEFENSE SYSTEMS LTD.

    发明人： SAROKA, Arie ,  SCHOENMANN, Amnon

    CPC分类号： B64C1/14 ,  B64C3/40 ,  B64C7/00 ,  B64C9/02 ,  F42B10/14 ,  F42B10/38 ,  Y02T50/14 ,  Y02T50/32

    摘要： A shutter mechanism for covering a wing's spreading opening formed in an airborne body and a method for covering such opening while implementing the shutter mechanism, wherein the shutter comprises at least one flap assembly, and wherein from the instant that a deployed wing of the airborne body passed and moved over it, it is biased by traction of at least one springy element to an angular motion around an axis, unto a condition where the flap component of the assembly is positioned so that it is substantially conformal to the outline of the outer surface of the fuselage of the airborne body and while it covers the opening through which the wing passed in its motion; and from an instant that the wing returned and connected to the flap component of the assembly, the flap is biased to an angular motion counter the spring, to the state that the wing returns and is relocated on its top surface.

    摘要翻译： 一种用于覆盖形成在空气传播体中的机翼传播开口的快门机构和一种在实现快门机构的同时覆盖这种开口的方法，其中快门包括至少一个挡板组件，并且其中从空中机体的部署翼 通过并在其上移动，它被至少一个弹性元件的牵引力偏压到围绕轴线的角运动，其中组件的折翼部件被定位成使得其基本上与外表面的轮廓一致 机身的机身，同时它覆盖机翼通过其运动的开口; 并且从翼返回并连接到组件的翼片部件的瞬间，翼片被偏压到与弹簧相反的角运动，到翼返回并被重新定位在其顶表面上的状态。

    CANARD-LOCKED OBLIQUE WING AIRCRAFT
    3.
    发明申请
    CANARD-LOCKED OBLIQUE WING AIRCRAFT 审中-公开
    CANARD-LOCKED OBLIQUE WING飞机

    公开(公告)号：WO2014134072A1

    公开(公告)日：2014-09-04

    申请号：PCT/US2014/018441

    申请日：2014-02-25

    申请人： NORTHROP GRUMMAN SYSTEMS CORPORATION

    发明人： SOMMER, Geoffrey S. ,  COTE, Kenneth A.

    IPC分类号： B64C3/40 ,  B64C5/04 ,  B64C30/00 ,  B64C39/12

    CPC分类号： B64C39/12 ,  B64C3/40 ,  B64C5/04 ,  B64C30/00 ,  Y02T50/14

    摘要： An aircraft includes a fuselage, a main wing pivotally coupled to an aft portion of the fuselage, and a canard coupled to a forward portion of fuselage, wherein the main wing and the canard are configured to be connected together for supersonic flight and disconnected from each other for subsonic flight.

    摘要翻译： 飞机包括机身，枢转地联接到机身的后部的主翼，以及耦合到机身的前部的鸭，其中所述主翼和所述挡板被构造成连接在一起用于超音速飞行并且与每个 其他为亚音速飞行。

    SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM
    4.
    发明申请
    SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM 审中-公开
    用于控制SONIC BOOM磁头的系统和方法

    公开(公告)号：WO2014126859A1

    公开(公告)日：2014-08-21

    申请号：PCT/US2014/015597

    申请日：2014-02-10

    申请人： GULFSTREAM AEROSPACE CORPORATION ,  FREUD, Donald

    发明人： FREUD, Donald

    IPC分类号： B64C30/00

    CPC分类号： B64C23/00 ,  B64C3/185 ,  B64C3/20 ,  B64C3/38 ,  B64C3/42 ,  B64C9/00 ,  B64C17/10 ,  B64C30/00 ,  B64D37/00 ,  Y02T50/14 ,  Y02T50/44

    摘要： A system for controlling a magnitude of a sonic boom includes a first sensor configured to detect a first condition of the supersonic aircraft. The system further includes a pair of wings configured to move fore and aft. The system further includes a processor communicatively coupled with the sensor and operatively coupled with the pair of wings. The processor is configured to (1) receive a first information from the first sensor indicative of the first condition, (2) calculate a lift distribution of the supersonic aircraft based on the first information, (3) determine an existence of a deviation of the lift distribution from a desired lift distribution based on the flight condition, and (4) control the pair of wings to move to redistribute the lift in a manner that more closely conforms to the desired lift distribution. The magnitude of the sonic boom is reduced when the deviation is reduced.

    摘要翻译： 用于控制声波起重臂的大小的系统包括被配置为检测超音速飞行器的第一状态的第一传感器。 该系统还包括一对构造成前后移动的翼。 所述系统还包括处理器，其与所述传感器通信地耦合并且与所述一对机翼可操作地耦合。 处理器被配置为（1）从第一传感器接收指示第一条件的第一信息，（2）基于第一信息计算超音速飞机的升力分布，（3）确定存在 基于飞行条件从所需的升力分布提升分配，以及（4）控制所述一对翼移动以以更符合期望的升力分布的方式重新分配升力。 当偏差减小时，声音臂的大小减小。

    VARIABLE GEOMETRY WING
    5.
    发明申请
    VARIABLE GEOMETRY WING 审中-公开
    可变几何

    公开(公告)号：WO2014041198A1

    公开(公告)日：2014-03-20

    申请号：PCT/EP2013/069291

    申请日：2013-09-17

    申请人： BLUE BEAR SYSTEMS RESEARCH LIMITED

    发明人： SNOOK, Michael Alexander

    IPC分类号： B64C3/40 ,  B64C3/54 ,  B64C33/02

    CPC分类号： B64C3/546 ,  B64C3/40 ,  B64C3/54 ,  B64C39/024 ,  B64C2003/543 ,  B64C2201/102 ,  Y02T50/14

    摘要： Embodiments of the present invention relate to an adaptable wing (112, 114) having a variable geometry for influencing aerodynamic performance, the wing (112, 114) comprising a jointed leading edge having a main pivot (116), and a wrist joint (118), with a wing arm (126, 128) therebetween, and a distal wing hand (122, 124) depending from the wrist joint (118); the wing (12, 114) being reciprocally actuable, via the main pivot (116) and wrist joint (118), between a first state having an extended wing planform and a second state having a tucked wing planform.

    摘要翻译： 本发明的实施例涉及一种具有可变几何形状以用于影响空气动力学性能的可适应翼（112,114），所述翼（112,114）包括具有主枢轴（116）和腕关节（118）的接合前缘 ），其间具有翼臂（126,128）和从腕关节（118）悬垂的远侧翼手（122,124）; 所述机翼（12,114）经由所述主枢轴（116）和腕关节（118）在具有延伸机翼平面图的第一状态和具有卷起的机翼平面图的第二状态之间可往复驱动。

    MORPHING WING FOR AN AIRCRAFT
    6.
    发明申请
    MORPHING WING FOR AN AIRCRAFT 审中-公开
    飞机的飞行员

    公开(公告)号：WO2013192483A1

    公开(公告)日：2013-12-27

    申请号：PCT/US2013/046952

    申请日：2013-06-21

    申请人： BOMBARDIER INC. ,  LEARJET INC. ,  XI, Fengfeng ,  FINISTAURI, Allan, Daniel ,  MOOSAVIAN, Amin

    发明人： XI, Fengfeng ,  FINISTAURI, Allan, Daniel ,  MOOSAVIAN, Amin

    IPC分类号： B64C3/44 ,  B64C3/52

    CPC分类号： B64C3/38 ,  B64C3/385 ,  B64C3/40 ,  B64C3/44 ,  B64C3/52 ,  B64C3/54 ,  B64C2003/445 ,  B64C2003/543 ,  Y02T50/14

    摘要： A morphing wing for an aircraft includes a top surface, a bottom surface, a leading edge, a trailing edge, a tip, and a root. A plurality of structural ribs (76,78) is disposed between the root and tip so that they extend between the top surface and the bottom surface and intersect with a lateral axis thereof. At least one active member (88,90,92,94) connects between two adjacent structural ribs along or at a first angle to the lateral axis. The active member is actively adjustable. At least one passive member (80,82,84,86) connects between the two adjacent structural ribs along or at a second angle to the lateral axis. The passive member is passively adjustable. Adjustment of at least one active member moves the adjacent structural ribs with respect to one another, thereby morphing the wing from a first configuration to a second configuration.

    摘要翻译： 用于飞机的变形翼包括顶表面，底表面，前缘，后缘，尖端和根部。 多个结构肋（76,78）设置在根部和尖端之间，使得它们在顶表面和底表面之间延伸并与其横向轴线相交。 至少一个有效构件（88,90,92,94）沿着或相对于横向轴线以第一角度连接在两个相邻的结构肋之间。 活动构件可以主动调节。 至少一个被动构件（80,82,84,86）沿着或相对于横向轴线的第二角度在两个相邻的结构肋之间连接。 被动构件被动调节。 至少一个活动构件的调节使相邻的结构肋相对于彼此移动，从而使机翼从第一构型变形到第二构型。

    AIRPLANE WING
    7.
    发明申请
    AIRPLANE WING 审中-公开
    飞机票

    公开(公告)号：WO2012040446A1

    公开(公告)日：2012-03-29

    申请号：PCT/US2011/052735

    申请日：2011-09-22

    申请人： HEATON, Clifford, D.

    发明人： HEATON, Clifford, D.

    IPC分类号： B64C39/00

    CPC分类号： B64C39/068 ,  B64C3/385 ,  B64C9/12 ,  B64C39/04 ,  B64C39/08 ,  B64D27/06 ,  B64D27/18 ,  Y02T50/14 ,  Y02T50/32 ,  Y10T29/49826

    摘要： An airplane wing configuration includes a first wing positioned above and forward of a second wing on an airplane fuselage. The first wing is operable to direct airflow over an upper surface of the second wing, whereby the first and second wings are capable of generating greater lift than a sum of their individual lifts. The first wing may include an adjustable wing flap that redirects airflow over the upper surface of the second wing, and the second wing may include a rotatable portion that pivots to vary the angle of attack of the second wing independent of the first wing.

    摘要翻译： 飞机机翼结构包括位于飞机机身上的第二机翼的上方和前方的第一机翼。 第一翼可操作以将气流引导到第二翼的上表面上，由此第一和第二翼能够产生比其各自升降机总和更大的升力。 第一翼可以包括可调节的翼片，其将气流重定向在第二翼的上表面上，并且第二翼可以包括枢转以可变地独立于第一翼的第二翼的迎角的可旋转部分。

    PERSONAL AIRCRAFT
    8.
    发明申请
    PERSONAL AIRCRAFT 审中-公开
    个人飞机

    公开(公告)号：WO2012012474A2

    公开(公告)日：2012-01-26

    申请号：PCT/US2011/044591

    申请日：2011-07-19

    申请人： ZEE.AERO INC. ,  KROO, Ilan

    发明人： KROO, Ilan

    IPC分类号： B64C29/00 ,  B64C27/12 ,  B64C27/08 ,  B64D41/00

    CPC分类号： B64C27/22 ,  B64C3/56 ,  B64C29/00 ,  B64C29/0025 ,  B64C39/08 ,  Y02T50/14 ,  Y02T50/145

    摘要： A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight.

    摘要翻译： 安全，安静，易于控制，高效和紧凑的飞机配置通过多个垂直提升转子，串联翼和前推推进器的组合实现。 垂直升降转子与前后翼结合，可以使电梯中心与垂直和水平飞行的重心平衡。 这种机翼和多转子系统能够容忍悬停，过渡或巡航飞行的有效载荷重量的较大变化，同时还提供垂直推力冗余。 推进系统使用多个提升转子和足够小尺寸的推进推进器，以防止潜在的叶片撞击，并为乘客提供更多的感知和真实的安全性。 使用多个独立的转子提供冗余和消除单点故障模式，使得车辆在飞行中不可操作。