Deployment brake release for a parachute
    41.
    发明授权
    Deployment brake release for a parachute 有权
    部署刹车释放降落伞

    公开(公告)号:US07648105B2

    公开(公告)日:2010-01-19

    申请号:US11645029

    申请日:2006-12-26

    Abstract: A deployment brake release system for use with an airborne guidance unit (AGU) of a parachute suitable for precision cargo delivery. The parachute includes deployment brake lines secured at one end to the edge of the canopy and connected at the other end through looped ends to motor control lines. The motor control lines are, in turn, engaged with the motor of the AGU. The deployment brake release system includes at least one hook mount having a hook secured to the AGU frame. The looped ends of the deployment brake lines are engaged with the hook during rigging so that, upon deployment, opening forces are applied to the hook mount rather than the motor. After full canopy inflation, the motor, via the motor control lines, pulls on the brake line looped ends to disengage them from the hook, transferring subsequent canopy loads to the AGU motor for the remainder of the flight. A method for releasing the deployment brake lines is also disclosed.

    Abstract translation: 与用于精密货物运送的降落伞的空中引导单元(AGU)一起使用的部署制动器释放系统。 降落伞包括一端固定在顶盖边缘的部署制动线,另一端通过环形端连接到电机控制线。 马达控制线又与AGU的马达接合。 部署制动器释放系统包括至少一个钩安装件,其具有固定到AGU框架上的钩子。 展开制动管线的环形端部在索具期间与钩接合,使得在展开时,打开力施加到钩安装件而不是马达。 在全冠层膨胀后,电机通过电机控制线拉动制动线环路端部,将其从钩上脱离,将剩余的顶盖负载转移到AGU电机,以用于其余的飞行。 还公开了一种用于释放展开制动线的方法。

    Inflatable aerodynamic wing and method
    42.
    发明授权
    Inflatable aerodynamic wing and method 失效
    充气气动翼和方法

    公开(公告)号:US07185851B2

    公开(公告)日:2007-03-06

    申请号:US10927579

    申请日:2004-08-26

    Applicant: Daryl B. Elam

    Inventor: Daryl B. Elam

    CPC classification number: B64C3/30 B64C39/024 B64C2201/105

    Abstract: An inflatable structure constructed of flexible material that can occupy a minimal volume when in a deflated and stored condition as compared to its fully inflated and deployed configuration, has sufficient structural rigidity to function as a wing when deployed. The wing includes an array of inflatable chambers with generally circular cross-sections. The chambers are spaced a particular distance between their centers and held in that spacing by an outer wing skin. For equal cross-sectional diameter chambers this distance is less than the diameter. When the chambers are inflated the close spacing causes tension in the opposing surfaces to create a rigid structure.

    Abstract translation: 与其完全膨胀和展开的构造相比,当处于放气和储存状态时可以占据最小体积的柔性材料构成的充气结构在展开时具有足够的结构刚度用作翼。 机翼包括具有大致圆形横截面的可充气室阵列。 这些室在它们的中心之间隔开特定的距离,并通过外翼皮保持在该间隔中。 对于等截面直径的腔室,该距离小于直径。 当室被充气时,紧密的间隔在相对的表面中产生张力以产生刚性结构。

    Stowable design for unmanned aerial vehicle
    43.
    发明申请
    Stowable design for unmanned aerial vehicle 审中-公开
    无人驾驶飞机的可存储设计

    公开(公告)号:US20060226280A1

    公开(公告)日:2006-10-12

    申请号:US11305524

    申请日:2005-12-16

    Applicant: James Alman

    Inventor: James Alman

    Abstract: An unmanned aerial vehicle (UAV) having a design for optimum stowability and low cost. The UAV having a collapsible wing section which can be easily removed from the fuselage, allowing for quick assembly and disassembly and ease of portability. The unmanned aerial vehicle includes a primary wing assembly, a fuselage, a means for propelling the unmanned aerial vehicle, and means for remotely controlling the unmanned aerial vehicle. The primary wing assembly includes a wing having a center spar and two outwardly diverging side spars. The wing also has a pliable flexible material supported by the center spar and the at least two outwardly diverging side spars. The pylon is connected to the wing and supports the wing. The fuselage is connected to the pylon such that the pylon extends away from the fuselage and spaces the wing a distance from the fuselage. The fuselage includes a tail having a rudder located along a trailing edge and elevators located along the trailing edge.

    Abstract translation: 无人飞行器(UAV)具有最佳的可收藏性和低成本的设计。 无人机具有可折叠的机翼部分,可以方便地从机身中移除,从而实现快速组装和拆卸,便于携带。 无人飞行器包括主翼组件,机身,用于推动无人驾驶飞行器的装置,以及用于远程控制无人驾驶飞行器的装置。 主翼组件包括具有中心翼梁和两个向外发散的侧翼的翼。 机翼还具有由中心翼梁和至少两个向外发散的侧翼支撑的柔韧的柔性材料。 塔架连接到机翼并支撑机翼。 机身连接到挂架,使得吊架远离机身延伸,并将机翼与机身隔开一段距离。 机身包括尾部,尾部沿着后缘设有方向舵,沿着后缘设有电梯。

    Stealthy duffel bag airplane
    44.
    发明授权
    Stealthy duffel bag airplane 失效
    隐形行李袋飞机

    公开(公告)号:US06892981B2

    公开(公告)日:2005-05-17

    申请号:US10408981

    申请日:2003-04-08

    Applicant: Jay Lipeles

    Inventor: Jay Lipeles

    Abstract: The Duffel Bag Airplane is an inflatable flying wing unmanned airborne vehicle (UAV). The fuselage will house everything but the wings. The wing can be rolled up around the fuselage into a small package when deflated for easy transportation, such as by being carried in a duffle bag. Fabric construction, a small internal combustion engine with cooled exhaust, and wing warping controls combine to make the airplane inexpensive and extremely stealthy. All the usual signatures have been suppressed, which allow it to be used to make observations from close range under combat conditions. Control of this airplane is accomplished by warping the wings and is supplemented with stability augmentation.

    Abstract translation: Duffel Bag飞机是一种充气飞翼无人机载机(UAV)。 机身将会容纳除翅膀之外的所有东西。 机翼可以卷绕在机身周围,当放气以便于运输时,例如通过携带在行李箱中,成为小包装。 织物结构,具有冷却排气的小型内燃机和机翼翘曲控制相结合,使飞机廉价而且非常隐蔽。 所有通常的签名已经被压制,这允许它用于在战斗条件下从近距离观察。 这架飞机的控制是通过扭转机翼来实现的,并补充了稳定性增强。

    Lightweight remotely controlled aircraft
    45.
    发明授权
    Lightweight remotely controlled aircraft 失效
    轻型遥控飞机

    公开(公告)号:US06793172B2

    公开(公告)日:2004-09-21

    申请号:US10296137

    申请日:2003-06-30

    Inventor: Lance A. Liotta

    Abstract: An aircraft which is designed for remote controlled slow flight, indoor or in a small outdoor yard or field. The aerial lifting body is defined by a series of lightweight planar or thin airfoil surfaces (A1, A2, A3, A4) arranged in a radially symmetrical configuration. Suspended within the cavity (O) formed by the thin airfoil surfaces (A1, A2, A3, A4) is a thrust generating propeller system (C) that is angled upwardly and that can be regulated remotely so as to change the angle of the thrust vector within the cavity (O) for steering. Lifting, stability, turning, and general control of the direction of motion in flight is accomplished without any formal wings, rudder, tail, or control surfaces.

    Abstract translation: 一种专为遥控慢速飞行,室内或室外小型场地设计的飞机。 升降体由一系列以径向对称构造布置的轻型平面或薄型翼型表面(A1,A2,A3,A4)限定。 悬挂在由薄翼面(A1,A2,A3,A4)形成的空腔(O)内的是推力发生螺旋桨系统(C),其向上倾斜并且可以远程调节,以便改变推力角 在腔(O)内的向量用于转向。 飞行中的运动方向的提升,稳定性,转向和一般控制是在没有任何正式的机翼,方向舵,尾翼或控制面的情况下完成的。

    Remote control powered parafoil aircraft
    46.
    发明申请
    Remote control powered parafoil aircraft 审中-公开
    远程控制动力parafoil飞机

    公开(公告)号:US20020193914A1

    公开(公告)日:2002-12-19

    申请号:US10045777

    申请日:2002-01-11

    Abstract: A remote-control powered parafoil aircraft has an aircraft body (1) that is engine powered and hung with lines (2) from an air-expandable wing (3, 30). The lines include control lines (15) with which air flow and aerodynamic shape of the air-expandable wing are variable selectively from a foil controller (18, 19, 20) on the aircraft body for flight-mode control. Sight from a television camera (8) on the aircraft body is televised to a control unit (9) from which control data is transmitted selectively from proximate the control unit to the foil controller (14) with a multi-axis joystick or similar control, to an engine (6) on the parafoil body from an engine controller (24) and to an item servo (29) for control of optional items (45) on the aircraft body.

    Abstract translation: 遥控动力的parafoil飞机具有发动机动力并悬挂有来自可膨胀翼(3,30)的线(2)的飞机主体(1)。 这些管线包括控制线(15),空气膨胀翼的空气流动和空气动力学形状可选择性地从飞行器体上的箔控制器(18,19,20)可变地进行飞行模式控制。 来自飞机机体上的电视摄像机(8)的视线被电视传送到控制单元(9),控制数据通过多轴操纵杆或类似的控制从控制单元的附近被选择性地发送到箔片控制器(14) 从发动机控制器(24)到达副翼车体上的发动机(6)和用于控制飞机主体上的可选项(45)的物品伺服(29)。

    Vehicle refueling system
    47.
    发明授权
    Vehicle refueling system 失效
    车辆加油系统

    公开(公告)号:US6142421A

    公开(公告)日:2000-11-07

    申请号:US231368

    申请日:1999-01-13

    Inventor: Miles R. Palmer

    Abstract: A vehicle refueling system includes an aero vehicle and a fuel bladder system. The fuel bladder system includes a fuel bladder, a pickup loop of a predetermined loop size, a reel mechanism to retract at least one side of the pickup loop to reduce the loop size, a snag sensor to sense when the pickup loop has been hooked by the retractable hook, the snag sensor initiating the reel mechanism, a compass to sense the random orientation of the loop, a radio navigation receiver to sense a location of the loop, and a transmitter to transmit the random orientation and the location. The vehicle includes a fuselage, a retractable hook with a hook sensor to detect when a fuel bladder is hooked and the loop size has been reduced by the reel mechanism, a fuel bladder stowage chamber within the fuselage, a fuel intake tube capable of drawing fuel from the fuel bladder stowed in the stowage chamber, a retraction mechanism to retract the retractable hook, a fuel transfer mechanism to transfer fuel from the fuel bladder into an internal fuel tank, and a fuel bladder discard mechanism to discard the fuel bladder after the fuel has been drawn from the fuel bladder.

    Abstract translation: 车辆加油系统包括航空车辆和燃料囊系统。 燃料囊系统包括燃料囊,预定环尺寸的拾取环,卷绕机构,用于缩回拾取环的至少一侧以减小环的尺寸;阻挡传感器,用于感测拾取环何时已被钩住 可伸缩钩,启动卷轴机构的阻塞传感器,用于感测环路的随机取向的罗盘,用于感测回路位置的无线电导航接收器,以及发送器,以发送随机取向和位置。 车辆包括机身,具有钩传感器的可伸缩钩,用于检测燃料囊何时被钩住,并且通过卷轴机构减小了环路尺寸,机身内部的燃料囊存放室,能够吸引燃料的燃料进入管 从装载在储存室中的燃料气囊,收回缩回钩的缩回机构,用于将燃料从燃料气囊输送到内部燃料箱中的燃料转移机构,以及在燃料之后废弃燃料气囊的燃料气体排出机构 已从燃油囊中抽出。

    Arrestment system
    48.
    发明授权
    Arrestment system 失效
    逮捕制度

    公开(公告)号:US4311290A

    公开(公告)日:1982-01-19

    申请号:US90205

    申请日:1979-11-01

    Inventor: Kenneth T. Koper

    Abstract: Apparatus and method for recovering and arresting an aircraft or other vele. A boom is swivelly connected to a support structure via braking mechanism. The boom is pivotally connected to the brake mechanism such that it can also pivot in a second, different plane intersecting the plane of rotation of the brake mechanism. A shear pin prevents pivoting of the boom in the second plane until the boom has experienced a predetermined load in that plane. The distal end of the boom distant from the brake mechanism is provided with structure for engaging the aircraft. When the aircraft is flown at and captured by the boom, the weight and motion of the aircraft breaks the shear pin, causing the boom to move in the second plane until engaged by a stop. This rapid change in position of the engaging end of the boom in the second plane prevents the aircraft from pendulating about the boom. Forward motion of the aircraft also causes movement within the brake mechanism in the first plane which absorbs the kinetic energy of the aircraft as the boom swivels against the brake mechanism, so that the aircraft is slowed and arrested.

    Abstract translation: 用于恢复和阻止飞机或其他车辆的装置和方法。 动臂通过制动机构旋转地连接到支撑结构。 吊杆枢转地连接到制动机构,使得其也可以在与制动机构的旋转平面相交的第二不同平面中枢转。 剪切销防止悬臂在第二平面中的枢转,直到悬臂在该平面中经历了预定的载荷。 离开制动机构的悬臂的远端设置有用于接合飞行器的结构。 当飞机飞行并被悬臂捕获时,飞行器的重量和运动会破坏剪切销,导致吊臂在第二平面中移动,直到停止。 在第二平面中,起重臂的接合端的这种快速变化防止飞机在吊杆周围摆动。 飞行器的前进运动也引起在第一平面内的制动机构内的运动,当悬臂靠在制动机构上转动时吸收飞行器的动能,从而使飞行器减慢和停止。

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