中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

115 records (took 0.017 seconds)

    Autonomous, back-packable computer-controlled breakaway unmanned aerial vehicle (UAV)
    71.
    发明授权
    Autonomous, back-packable computer-controlled breakaway unmanned aerial vehicle (UAV) 失效
    自主的，可回填计算机控制的无人机（UAV）

    公开(公告)号：US07237750B2

    公开(公告)日：2007-07-03

    申请号：US10976153

    申请日：2004-10-29

    Applicant: Tien Seng Chiu ,  Jay Willmott

    Inventor： Tien Seng Chiu ,  Jay Willmott

    IPC: B64C1/00

    CPC classification number: B64C1/00 ,  A45C5/00 ,  A45C13/02 ,  B64C1/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/165 ,  B64C2201/187 ,  B64C2201/201 ,  B64C2201/203

    Abstract: A modular unmanned aerial vehicle (UAV) having a fuselage, a nose cone, a left wing piece, a right wing piece, and a tail section. The tail section and nose cone each join to the fuselage through mating bulkhead structures that provide quick connection capability while being readily separated so as to enable the UAV to break apart at these connection points and thereby absorb or dissipate impact upon landing. The UAV is capable of rapid assembly in the field for two-man launch and data retrieval, as well as quick disassembly into these five component parts for transport and storage in a highly compact transport case that can be carried as a backpack.

    Abstract translation: 具有机身，鼻锥，左翼片，右翼片和尾部的模块化无人驾驶飞行器（UAV）。 尾部和鼻锥每个通过配合的隔板结构连接到机身，提供快速的连接能力，同时易于分离，以便使UAV在这些连接点处分裂，从而吸收或消散着陆时的冲击。 无人机能够在现场快速组装两人发射和数据检索，以及快速拆卸到这五个部件中，用于运输和存储，可以作为背包携带的高度紧凑的运输箱。

    Autonomous control of a parafoil recovery system for UAVs
    72.
    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。

    Small-sized radio-controlled flying device
    74.
    发明申请
    Small-sized radio-controlled flying device 失效
    小型无线电遥控飞行装置

    公开(公告)号：US20020190157A1

    公开(公告)日：2002-12-19

    申请号：US10168588

    申请日：2002-06-24

    Inventor： Jean Asseline ,  George De Noni

    IPC: B64C001/00 ,  B64C003/00 ,  B64C005/00 ,  B64C007/00

    CPC classification number: A63H27/08 ,  A63H30/04 ,  B64C2201/086 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/187 ,  Y10S244/902 ,  Y10S244/903

    Abstract: This invention relates to a small-sized radio controlled flying device propelled by a thermal engine (20) with pusher type airscrew (19) for remote sensing, said device enabling short take-off and landing and flying at maximum speed of 35 Km/h. The device comprises a pod and wings, the pod (1) being a rigid tricycle carriage dismountable by disengagement of substantially pyramidal jig with rear base (2) and front apex (7), lower plane (3), two lateral planes (4, 5) and an upper plane (6), the base being a welded one-piece element and comprising the engine, the airscrew, a tank and the radio control, the apex being a welded one-piece element, the lower plane and the two lateral planes comprising spars (11, 12) at least assembled at the base and at the apex, the lower plane comprising at its three end angles two rear wheels (8) and a front wheel (9), the front wheel being provided to protrude towards the front in the apex and the wheels being low pressure tires, the wings (13) being a caisson-type supple parachute, said wings being connected to the pod in an adjustable fashion by two front slings (17), two braking slings (18) acting on the two flaps/ailerons.

    Abstract translation: 本发明涉及一种由具有用于遥感的推进式螺旋桨（19）的热引擎（20）推进的小型无线电控制飞行装置，所述装置能够以35Km / h的最大速度进行短时起飞和着陆和飞行 。 该装置包括荚和翼，所述荚（1）是刚性三轮车，通过基本上棱锥形的夹具与后基部（2）和前顶点（7），下平面（3），两个侧平面（4， 5）和上平面（6），底座是焊接的整体元件，包括发动机，螺旋桨，水箱和无线电控制器，顶点是焊接的一体元件，下平面和两个 包括至少在基部和顶点处组装的翼梁（11,12）的横向平面，所述下平面在其三个端角处包括两个后轮（8）和前轮（9），所述前轮设置成突出 朝向顶端的前部并且车轮是低压轮胎，翼（13）是沉箱式柔软的降落伞，所述翼以可调节的方式通过两个前吊索（17），两个制动吊索（ 18）作用于两个翼片/副翼。

    Liquid hydrogen aircraft
    76.
    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
    77.
    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。

Patent Agency Ranking