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    TRANSMISSION FOR A COAXIAL COUNTER ROTATING ROTOR SYSTEM
    141.
    发明申请
    TRANSMISSION FOR A COAXIAL COUNTER ROTATING ROTOR SYSTEM 有权
    同轴旋转转子系统传动

    公开(公告)号：US20030218093A1

    公开(公告)日：2003-11-27

    申请号：US10153970

    申请日：2002-05-23

    Inventor： Vincent Francis Millea ,  Anthony George Chory ,  Michelle Consolini ,  Ralph D. Costanzo ,  Jules G. Kish

    IPC: B64D035/00

    CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/165 ,  B64D35/06

    Abstract: A transmission system for a hybrid aircraft is driven by a plurality of driveshafts and drives a translational propulsion system. Each driveshaft is mounted to a pinion gear which mesh with an upper and lower counter-rotating gear. The upper and lower counter-rotating gears drive a respective upper and lower rotor shaft which powers a counter-rotating rotor system. A first angle is defined between a first and a second driveshaft while a second angle is defined between the second and a third driveshaft. The angle between the driveshafts are a whole number multiple of the formula: nullnull(CP/R)*(180/null). By so angularly locating the driveshafts, proper meshing of the pinion gears and the upper and lower counter-rotating gears is assured and tolerances are less stringent as the support structure is effective designed around optimal location of the driveshafts for gear meshing rather than vice versa.

    Abstract translation: 用于混合飞机的传动系统由多个驱动轴驱动并驱动平移推进系统。 每个驱动轴安装在与上下反转齿轮啮合的小齿轮上。 上下反转齿轮驱动相应的上下转子轴，其对反向旋转的转子系统供电。 在第一和第二驱动轴之间限定第一角度，而在第二和第三驱动轴之间限定第二角度。 驱动轴之间的角度是以下公式的整数倍：θ=（CP / R）*（180 / pi）。 通过如此角度地定位传动轴，确保小齿轮和上下相对转动齿轮的适当啮合，并且由于支撑结构有效地围绕用于齿轮啮合的驱动轴的最佳位置设计而不是反之亦然，公差不太严格。

    Autonomous control of a parafoil recovery system for UAVs
    142.
    发明申请
    Autonomous control of a parafoil recovery system for UAVs 审中-公开
    无人机的parafoil恢复系统的自主控制

    公开(公告)号：US20030025038A1

    公开(公告)日：2003-02-06

    申请号：US09922167

    申请日：2001-08-06

    Applicant: Lockheed Martin Corporation

    Inventor： Leland M. Nicolai ,  Douglas J. Robinson ,  William R. Ramsey JR.

    IPC: B64D017/14 ,  B64D017/18 ,  B64D017/34

    CPC classification number: G05D1/105 ,  B64C39/024 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/185 ,  B64C2201/187 ,  B64D17/025 ,  B64D17/343

    Abstract: A parafoil system for autonomously controlling the gliding descent of a payload/UAV from a launch point to a predetermined recovery area and manipulating the parafoil to execute a soft landing in the recovery area, a sensing means associated with the system for determining wind speed and direction, as well as altitude, heading and position of the system, a means housed within the system for processing information received from the sensing means to determine the gliding flight path from the launch point to a predetermined recovery area and the execution of a flare maneuver to achieve a soft landing, control surface means on the parafoil canopy, mechanical means coupling the information processing means with the control surface means for adjusting the control surface means to accomplish the steering to the recovery area during gliding flight and the flare maneuver during landing, and a power source in the payload/UAV.

    Abstract translation: 一种用于自主地控制有效载荷/ UAV从发射点到预定恢复区域的滑翔下降并操纵石灰石以在恢复区域中执行软着陆的石蜡系统系统，与用于确定风速和方向的系统相关联的感测装置 ，以及系统的高度，航向和位置，装在系统内的装置，用于处理从感测装置接收的信息，以确定从发射点到预定恢复区域的滑行飞行路径，以及执行火炬操纵 实现软着陆，控制表面装置在parafoil冠层上，机械装置将信息处理装置与控制面相结合，用于调整控制面装置，以实现滑行飞行期间的恢复区域的转向和着陆期间的火炬机动，以及 有效载荷/无人机中的电源。

    Method and apparatus for retrieving a flying object
    144.
    发明申请
    Method and apparatus for retrieving a flying object 审中-公开
    用于检索飞行物体的方法和装置

    公开(公告)号：US20020100838A1

    公开(公告)日：2002-08-01

    申请号：US10013094

    申请日：2001-10-29

    Inventor： Brian T. McGeer ,  Andreas H. von Flotow ,  Cory Roeseler ,  Clifford Jackson

    IPC: B64F001/12

    CPC classification number: B64C39/024 ,  B64C25/68 ,  B64C2201/104 ,  B64C2201/148 ,  B64C2201/182 ,  B64C2201/205 ,  B64F1/02

    Abstract: A method and an apparatus for capturing a flying object (5) are revealed. The apparatus includes a generally linear fixture (2), such as a length of rope; a means for suspending (1) the fixture (2) across the path of the flying object (5); and one or more hooks (19) on the flying object (5). The method involves suspending the fixture (2) such that its orientation includes a component normal to the flying object's line of approach; striking the fixture (2) with the flying object (5), which causes the flying object (5) to rotate and decelerate, while the fixture (2) slides along a surface of the flying object (5) into a hook (19); capturing the fixture (2) in the hook (19); and retrieving the flying object (5) from the fixture (2).

    Abstract translation: 揭示了用于捕获飞行物体（5）的方法和装置。 该装置包括大致线性的固定装置（2），例如一段绳索; 用于将（1）固定装置（2）悬挂在飞行物体（5）的路径上的装置; 和飞行物体（5）上的一个或多个钩（19）。 该方法涉及将固定装置（2）悬挂使得其取向包括垂直于飞行物体接近线的部件; （2）沿着飞行物体（5）的表面滑动到钩（19）中时，使飞行物体（5）与飞行物体（5）撞击，使飞行物体（5）旋转和减速， ; 捕获挂钩（19）中的固定装置（2）; 以及从所述固定装置（2）检索所述飞行物体（5）。

    Liquid hydrogen aircraft
    146.
    发明申请
    Liquid hydrogen aircraft 审中-公开
    液氢飞机

    公开(公告)号：US20020070312A1

    公开(公告)日：2002-06-13

    申请号：US10073518

    申请日：2002-02-11

    Inventor： Paul B. MacCready ,  Bart D. Hibbs ,  Robert F. Curtin ,  Kyle D. Swanson ,  Paul Belik

    IPC: B64B001/20 ,  B64C001/00 ,  B64C017/00

    CPC classification number: B64D27/24 ,  B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187 ,  B64D27/02 ,  B64D37/30 ,  B64D2041/005 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44 ,  Y02T50/64 ,  Y02T90/36

    Abstract: Disclosed is an aircraft, configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The aircraft includes an extendable slat at the leading edge of the wing, and a reflexed trailing edge. The aircraft comprises a flying wing extending laterally between two ends and a center point. The wing is swept and has a relatively constant chord. The aircraft also includes a power module configured to provide power via a fuel cell. The fuel cell stores liquid hydrogen as fuel, but uses gaseous hydrogen in the fuel cell. A fuel tank heater is used to control the boil-rate of the fuel in the fuel tank. The aircraft of the invention includes a support structure including a plurality of supports, where the supports form a tetrahedron that affixes to the wing.

    Abstract translation: 公开了一种被配置为具有宽范围的飞行速度的飞机，在延长的时间段内消耗低水平的功率，同时以无阻碍的向下观看的方式支持通信平台。 飞机在翼的前缘包括可延伸的板条，以及反射的后缘。 飞机包括在两端之间横向延伸的飞翼和中心点。 机翼被扫掠并具有相对恒定的和弦。 该飞机还包括被配置为经由燃料电池提供电力的功率模块。 燃料电池将液态氢作为燃料储存，而在燃料电池中使用气态氢。 燃料箱加热器用于控制燃料箱中的燃料的沸腾率。 本发明的飞行器包括支撑结构，该支撑结构包括多个支撑件，其中支撑件形成固定在机翼上的四面体。

    STOL/VTOL free wing aircraft with improved shock dampening and absorbing means
    148.
    发明授权
    STOL/VTOL free wing aircraft with improved shock dampening and absorbing means 失效
    STOL / VTOL自由翼飞机具有改进的减震和吸收手段

    公开(公告)号：US5863013A

    公开(公告)日：1999-01-26

    申请号：US467107

    申请日：1995-06-06

    Applicant: Hugh Schmittle

    Inventor： Hugh Schmittle

    IPC: B64C3/38 ,  B64C29/00 ,  B64C39/02 ,  B64C39/04

    CPC classification number: B64C39/04 ,  B64C29/0033 ,  B64C3/385 ,  B64C39/024 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187

    Abstract: An improved VTOL/STOL free wing aircraft providing damping and absorption of shock landing loads upon landing. A pair of resilient struts is provided, projecting forwardly from the trailing edge of either side of the fuselage when the fuselage is tilted. Preferably, the aircraft includes a pair of articulated tail booms, the strut being a portion of the tail boom extending forward from the pivot axis of the tail boom. Landing wheels are disposed on the strut in tandem spaced relationship. The resiliency of the strut causes the strut to act as a leaf spring and thus dampen shock landing loads. Operatively secured to the bottom surface of the fixed wing portions and the forward portion of the landing gear struts is a pair of dashpots for absorbing the shock landing loads.

    Abstract translation: 改进的VTOL / STOL自由翼飞机在着陆时提供减震和吸收冲击着陆载荷。 当机身倾斜时，提供一对弹性支柱，从机身任一侧的后缘向前突出。 优选地，飞行器包括一对铰接的尾臂，支柱是从尾臂的枢转轴线向前延伸的尾臂的一部分。 着陆轮以串联间隔的关系设置在支柱上。 支柱的弹性导致支柱作为板簧，从而抑制冲击着陆载荷。 操作地固定到固定翼部分的底表面和起落架支柱的前部是用于吸收冲击着陆载荷的一对减震器。

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