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    SYSTEMS AND DEVICES FOR REMOTELY OPERATED UNMANNED AERIAL VEHICLE REPORT-SUPPRESSING LAUNCHER WITH PORTABLE RF TRANSPARENT LAUNCH TUBE
    152.
    发明申请
    SYSTEMS AND DEVICES FOR REMOTELY OPERATED UNMANNED AERIAL VEHICLE REPORT-SUPPRESSING LAUNCHER WITH PORTABLE RF TRANSPARENT LAUNCH TUBE 有权
    用于远程操作的无人驾驶航空器报警系统和设备 - 带便携式射频透明发射管的超级发射器

    公开(公告)号：US20110315817A1

    公开(公告)日：2011-12-29

    申请号：US13229377

    申请日：2011-09-09

    Applicant: Carlos Thomas Miralles ,  Guan H. Su ,  Oleksandr Andryukov ,  John McNeil

    Inventor： Carlos Thomas Miralles ,  Guan H. Su ,  Oleksandr Andryukov ,  John McNeil

    IPC: B64F1/04

    CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/201 ,  B64F1/06 ,  F41A21/02 ,  F41F1/00 ,  F41F3/042 ,  F42B39/14

    Abstract: An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node.

    Abstract translation: 一种无人驾驶飞行器（UAV）发射管，其包括被配置为将UAV接合在由内壁限定的发射器体积内的拴系的艉板，所述拴系的突出部的尺寸被设计成在内壁处提供压力密封并且系在内壁上，以及 其中所述系留式破碎器是中空的，其具有朝向高压容积的开口端，并且连接在所述破坏物的中空部内并且附接到保持高压容积的内壁或附接到内底壁的内壁的系绳。 一种包括通信节点和发射器的系统，其包括处于预发射状态的无人驾驶飞行器（UAV），其被配置为接收并响应来自所述通信节点的命令输入。

    Telescoping and sweeping wing that is reconfigurable during flight
    153.
    发明申请
    Telescoping and sweeping wing that is reconfigurable during flight 审中-公开
    在飞行中可重构的伸缩和扫掠翼

    公开(公告)号：US20110001016A1

    公开(公告)日：2011-01-06

    申请号：US12314534

    申请日：2008-12-12

    Applicant: Robert Stewart Skillen ,  Raymond Charles Jones ,  Ross Michael Jones

    Inventor： Robert Stewart Skillen ,  Raymond Charles Jones ,  Ross Michael Jones

    IPC: B64C3/54 ,  B64D37/04

    CPC classification number: B64D37/14 ,  B64C3/40 ,  B64C3/54 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/127

    Abstract: An aircraft wing includes a stationary root section and a telescoping end section slideable in the span wise direction, where the loads for the root and extendable end sections are carried predominately by the airfoil composite skins, rather than a framework of spars and ribs as in conventional aircraft wings. In a single-telescoping configuration the telescoping end section slides within the root section as it extends and retracts during flight, and in another, the telescoping end section slides over the root section as it extends and retracts during flight. The aircraft wing can also include a second telescoping distal end section, and can sweep back during flight, while the end sections or distal end sections are extended or retracted.

    Abstract translation: 飞行器机翼包括固定的根部段和可在跨度方向上滑动的伸缩端部，其中根部和可延伸的端部的负载主要由翼型复合材料外壳承载，而不是如常规的翼梁和肋骨框架 飞机机翼。 在单伸缩构型中，伸缩端部在飞行过程中延伸和缩回时在根部段内滑动，并且在另一方面，伸缩端部在飞行期间延伸和缩回时滑过根部。 飞行器机翼还可以包括第二伸缩远端部分，并且在飞行期间可以向后扫掠，同时端部部分或远端部分延伸或缩回。

    MULTI-LAYER METAL/SHAPE MEMORY POLYMER ROLL-UP WING STRUCTURES FOR FITMENT-CONSTRAINED AIR VEHICLES
    154.
    发明申请
    MULTI-LAYER METAL/SHAPE MEMORY POLYMER ROLL-UP WING STRUCTURES FOR FITMENT-CONSTRAINED AIR VEHICLES 有权
    多层金属/形状记忆聚合物旋转翼型结构

    公开(公告)号：US20100282906A1

    公开(公告)日：2010-11-11

    申请号：US12463400

    申请日：2009-05-10

    Applicant: Terry M. Sanderson ,  Brian J. Gowler ,  David R. Sar ,  Thomas P. McCreery

    Inventor： Terry M. Sanderson ,  Brian J. Gowler ,  David R. Sar ,  Thomas P. McCreery

    IPC: B64C3/00 ,  B64C1/00

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/201 ,  F42B10/14 ,  F42B10/146 ,  F42B10/16 ,  F42B10/20

    Abstract: A laminated wing structure includes at least one layer of metal material and at least one layer of a shape memory polymer (SMP) material. The SMP is heated to a temperature in its glass transition band Tg to roll the wing around the air vehicle into a stored position. The metal layer(s) must be thin enough to remain below its yield point when rolled up. In preparation for launch, the SMP material is thermally activated allowing the strain energy stored in the layer of metal material to return the wing to its deployed position at launch. Once deployed, the SMP cools to its glassy state. The SMP material may be reinforced with fiber to form a polymer matrix composite (PMC). SMP may be used to provide shear strain relief for multiple metal layers. By offloading the motive force required to return the wing to its original deployed position from the SMP to the metal, the polymer does not acquire a permanent set and the wing may be deployed accurately.

    Abstract translation: 层压翼结构包括至少一层金属材料和至少一层形状记忆聚合物（SMP）材料。 将SMP加热到其玻璃化转变带Tg的温度，以将机身周围的机翼卷绕成储存位置。 金属层必须足够薄以便在卷起时保持低于其屈服点。 在准备发射时，SMP材料被热激活，允许存储在金属材料层中的应变能在发射时将机翼返回到其展开位置。 一旦部署，SMP冷却到玻璃状态。 SMP材料可以用纤维增强以形成聚合物基质复合材料（PMC）。 SMP可用于为多个金属层提供剪切应变消除。 通过卸载将机翼从SMP返回到金属的原始展开位置所需的动力，聚合物不会获得永久变形，并且可以准确地展开机翼。

    Air vehicle wing pivot
    155.
    发明授权
    Air vehicle wing pivot 有权
    机动车翼枢轴

    公开(公告)号：US07816635B2

    公开(公告)日：2010-10-19

    申请号：US11934083

    申请日：2007-11-02

    Applicant: Lawrence E. Fink

    Inventor： Lawrence E. Fink

    IPC: F42B10/14

    CPC classification number: B64C3/56 ,  B64C39/024 ,  B64C2201/102 ,  F42B10/14 ,  F42B15/105 ,  Y02T50/14

    Abstract: A stowable wing structure incorporates a wing having a span equal to a fuselage length and movable from a stowed position longitudinally aligned with the fuselage to a deployed position perpendicular to the fuselage. A pivot offset laterally from a centerline of the fuselage and aft from a symmetry point on the centerline with a corresponding offset forward toward the leading edge from a chord centerpoint on the wing allows rotation of the wing from the stowed position to the deployed position with the rotation resulting in an aft position of the chord center point relative to the fuselage symmetry point.

    Abstract translation: 可收起的机翼结构包括具有等于机身长度的跨度的翼，并且可以从与机身纵向对齐的收起位置移动到垂直于机身的展开位置。 从机身的中心线横向偏离的枢轴和来自中心线上的对称点的后部具有从机翼上的弦中心点朝向前缘的相应偏移，允许机翼从收起位置旋转到展开位置， 旋转导致弦中心点相对于机身对称点的后部位置。

    Air Vehicle Wing Pivot
    157.
    发明申请
    Air Vehicle Wing Pivot 有权
    机动车翼数据透视

    公开(公告)号：US20100038470A1

    公开(公告)日：2010-02-18

    申请号：US11934083

    申请日：2007-11-02

    Applicant: Lawrence E. Fink

    Inventor： Lawrence E. Fink

    IPC: B64C3/56

    CPC classification number: B64C3/56 ,  B64C39/024 ,  B64C2201/102 ,  F42B10/14 ,  F42B15/105 ,  Y02T50/14

    Abstract: A stowable wing structure incorporates a wing having a span equal to a fuselage length and movable from a stowed position longitudinally aligned with the fuselage to a deployed position perpendicular to the fuselage. A pivot offset laterally from a centerline of the fuselage and aft from a symmetry point on the centerline with a corresponding offset forward toward the leading edge from a chord centerpoint on the wing allows rotation of the wing from the stowed position to the deployed position with the rotation resulting in an aft position of the chord center point relative to the fuselage symmetry point.

    Abstract translation: 可收起的机翼结构包括具有等于机身长度的跨度的翼，并且可以从与机身纵向对齐的收起位置移动到垂直于机身的展开位置。 从机身的中心线横向偏离的枢轴和来自中心线上的对称点的后部具有从机翼上的弦中心点朝向前缘的相应偏移，允许机翼从收起位置旋转到展开位置， 旋转导致弦中心点相对于机身对称点的后部位置。

    DEPLOYMENT OF TELESCOPING AIRCRAFT STRUCTURES BY DROGUE PARACHUTE RISER TENSION
    158.
    发明申请
    DEPLOYMENT OF TELESCOPING AIRCRAFT STRUCTURES BY DROGUE PARACHUTE RISER TENSION 审中-公开
    通过喷雾器上升张力来调用飞机结构

    公开(公告)号：US20090314886A1

    公开(公告)日：2009-12-24

    申请号：US12137901

    申请日：2008-06-12

    Applicant: Tom Clancy ,  Robert Parks

    Inventor： Tom Clancy ,  Robert Parks

    IPC: B64C1/00 ,  B64C3/56 ,  B64C25/10

    CPC classification number: B64C3/56 ,  B64C25/20 ,  B64C39/024 ,  B64C2201/102 ,  B64D17/80 ,  Y10T24/39

    Abstract: A system for deploying a deployable structure in an aircraft, comprising a drogue parachute, at least one deployable structure, a riser line attached to the drogue parachute and the at least one deployable structure, wherein when the drogue parachute is deployed, a tension is applied to the riser line, and a parachute deployment system, wherein the parachute deployment system is configured to utilize the applied tension to deploy the at least one deployable structure.

    Abstract translation: 一种用于在飞行器中部署可部署结构的系统，包括锥形降落伞，至少一个可部署结构，连接到锥形降落伞和至少一个可展开结构的提升管线，其中当锥形降落伞被部署时，施加张力 升降机线路和降落伞部署系统，其中所述降落伞部署系统被配置为利用所施加的张力部署所述至少一个可部署结构。

    AIRCRAFT WING
    160.
    发明申请
    AIRCRAFT WING 审中-公开
    飞机票

    公开(公告)号：US20090008507A1

    公开(公告)日：2009-01-08

    申请号：US12058482

    申请日：2008-03-28

    Applicant: Jerome Pearson

    Inventor： Jerome Pearson

    IPC: B64C3/26 ,  B64C13/16

    CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/102

    Abstract: A powered aircraft wing is described including a flexible solid sheet having energy cells integrated with the sheet.

    Abstract translation: 描述了一种动力飞行器机翼，其包括具有与该片材一体化的能量单元的柔性固体片。

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