中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

79 records (took 0.022 seconds)

    SYSTEMS AND METHODS FOR CAPTURING AND CONTROLLING POST-RECOVERY MOTION OF UNMANNED AIRCRAFT
    12.
    发明申请
    SYSTEMS AND METHODS FOR CAPTURING AND CONTROLLING POST-RECOVERY MOTION OF UNMANNED AIRCRAFT 有权
    用于捕获和控制未经规定的飞机的恢复后运动的系统和方法

    公开(公告)号：US20100025528A1

    公开(公告)日：2010-02-04

    申请号：US11775600

    申请日：2007-07-10

    Applicant: Clifford Jackson

    Inventor： Clifford Jackson

    IPC: B64F1/02

    CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/086 ,  B64C2201/165 ,  B64C2201/182

    Abstract: Systems and methods for capturing and controlling post-recovery motion of an unmanned aircraft are disclosed herein. An aircraft system in accordance with one embodiment of the invention, for example, can include a line capture assembly carried by an unmanned aircraft having a fuselage and a lifting surface. The line capture assembly can include a flexible support line having a first portion attached to an attachment point on the fuselage and a second portion extending from the attachment point spanwise along the lifting surface of the aircraft. The line capture assembly can also include an engagement device coupled to the second portion of the support line. The engagement device is releasably secured to the lifting surface.

    Abstract translation: 本文公开了用于捕获和控制无人飞行器的恢复后运动的系统和方法。 例如，根据本发明的一个实施例的飞行器系统可以包括由具有机身和提升表面的无人飞行器承载的线捕获组件。 线捕获组件可以包括柔性支撑线，其具有附接到机身上的附接点的第一部分和从飞行器的提升表面沿着方向从附接点延伸的第二部分。 线捕获组件还可以包括联接到支撑线的第二部分的接合装置。 接合装置可释放地固定到提升表面。

    METHODS AND APPARATUS FOR AIRCRAFT
    13.
    发明申请
    METHODS AND APPARATUS FOR AIRCRAFT 有权
    航空器的方法和装置

    公开(公告)号：US20080277524A1

    公开(公告)日：2008-11-13

    申请号：US12100252

    申请日：2008-04-09

    Applicant: KEITH M. BROCK

    Inventor： KEITH M. BROCK

    IPC: B64C1/26

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/086

    Abstract: Methods and apparatus for aircraft according to various aspects of the present invention operate in conjunction with a fuselage and a wing. The fuselage may be configured to generate lift in response to airflow over the fuselage. In addition, the fuselage may have at least one hole defined therethrough. A spar may be disposed through the hole and extend into at least a portion of the wing and at least a portion of the fuselage. The spar may connect the fuselage to the wings.

    Abstract translation: 根据本发明的各个方面的用于飞行器的方法和装置与机身和机翼结合操作。 机身可以配置成响应于机身上的气流产生升力。 此外，机身可以具有穿过其中限定的至少一个孔。 翼梁可以穿过孔布置并延伸到机翼的至少一部分和机身的至少一部分。 翼梁可以将机身连接到机翼上。

    Small-sized radio-controlled flying device
    15.
    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
    17.
    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
    18.
    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