中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

88 records (took 0.023 seconds)

    Wireless-controlled airplane
    31.
    发明申请
    Wireless-controlled airplane 失效
    无线控制的飞机

    公开(公告)号：US20070084971A1

    公开(公告)日：2007-04-19

    申请号：US11252185

    申请日：2005-10-18

    Applicant: Haru Miyake

    Inventor： Haru Miyake

    IPC: B64C13/20

    CPC classification number: B64C13/20 ,  A63H27/007 ,  A63H27/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/165

    Abstract: A wireless-controlled airplane includes a flying unit and an on-ground controller which is connected to the flying unit through a communication section and flies the flying unit. The flying unit includes a body, a drive section installed on the body, a propulsion apparatus which generates a propulsive force when driven by the drive section, a main wing including a plurality of wing elements which are installed so as to be able to move with respect to each other, an opening and closing mechanism which changes the relative positions of the wing elements to change the effective area of the main wing, and a dropping apparatus which selectively holds and drops a load. By changing the effective area of the main wing, the flight speed can be changed, so the capacity and size of the drive section for rotating the propulsion apparatus can be decreased.

    Abstract translation: 无线控制飞机包括飞行单元和地面控制器，其通过通信部分连接到飞行单元并飞行飞行单元。 飞行单元包括主体，安装在主体上的驱动部分，当由驱动部驱动时产生推进力的推进装置，包括多个翼元件的主翼，其安装成能够与 相对于彼此相对的改变主翼的有效面积而改变翼元件的相对位置的开闭机构，以及选择性地保持和降低载荷的下落装置。 通过改变主翼的有效面积，可以改变飞行速度，因此可以减小用于旋转推进装置的驱动部的容量和尺寸。

    Inflatable aerodynamic wing and method
    32.
    发明申请
    Inflatable aerodynamic wing and method 失效
    充气气动翼和方法

    公开(公告)号：US20060060706A1

    公开(公告)日：2006-03-23

    申请号：US10927579

    申请日：2004-08-26

    Applicant: Daryl Elam

    Inventor： Daryl Elam

    IPC: B64B1/58

    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。

    Small-sized radio-controlled flying device
    33.
    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。

    Inflatable airfoil system having reduced radar observability
    36.
    发明授权
    Inflatable airfoil system having reduced radar observability 有权

    公开(公告)号：US09988138B2

    公开(公告)日：2018-06-05

    申请号：US14250385

    申请日：2014-04-11

    Applicant: The Boeing Company

    Inventor： Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

    IPC: B64C3/30 ,  B64C39/02

    CPC classification number: B64C3/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/105

    Abstract: A method and apparatus for operating an airfoil system. A gas may be generated. The gas may be sent into an inflatable airfoil system comprising an inflatable air foil and a section. The inflatable airfoil may have an inner end and an outer end in which the inflatable airfoil may be comprised of a number of materials that substantially pass electromagnetic waves through the inflatable airfoil. The section may have a number of openings in which the inner end of the inflatable airfoil may be associated with the section. The section may be configured to be associated with a fuselage. The number of openings may be configured to provide communications with an interior of the inflatable airfoil. The section with the number of openings may be configured to reduce reflection of the electromagnetic waves encountering the section.

    Adaptable solar airframe with a flexible photovoltaic system
    38.
    发明授权
    Adaptable solar airframe with a flexible photovoltaic system 有权
    具有柔性光伏系统的适应性太阳能机身

    公开(公告)号：US09067668B2

    公开(公告)日：2015-06-30

    申请号：US14091969

    申请日：2013-11-27

    Applicant: SUNLIGHT PHOTONICS INC.

    Inventor： John Peter Moussouris ,  Sergey V. Frolov ,  Michael Cyrus

    IPC: B64C3/46 ,  B64C1/00 ,  B64C1/34 ,  B64C39/02 ,  G01S3/786

    CPC classification number: B64C1/0009 ,  B64C1/34 ,  B64C3/46 ,  B64C39/024 ,  B64C2201/105 ,  B64D2211/00 ,  G01S3/7861 ,  Y02T50/14

    Abstract: Methods and apparatus for an adaptable solar airframe are provided herein. In some embodiments, an adaptable solar airframe includes an expandable body having an aerodynamic cross-section that reduces parasitic air drag at any given thickness of the body, further being able to change its shape in flight in response to changes in the relative position of the sun; and a flexible solar PV system attached to the surface of the expandable body.

    Abstract translation: 本文提供了适用于太阳能机身的方法和装置。 在一些实施例中，可适应的太阳能机身包括具有空气动力学横截面的可膨胀体，该横截面减小了任何给定厚度的身体的寄生空气阻力，并且还能够响应于相对位置的变化而改变其在飞行中的形状 太阳; 以及附接到可膨胀体表面的柔性太阳能光伏系统。

    Automatic takeoff method for an aircraft with a flexible airfoil, and airfoil and aircraft
    39.
    发明授权
    Automatic takeoff method for an aircraft with a flexible airfoil, and airfoil and aircraft 有权
    具有柔性翼型，翼型和飞机的飞机的自动起飞方法

    公开(公告)号：US08855838B2

    公开(公告)日：2014-10-07

    申请号：US13381197

    申请日：2009-10-28

    Applicant: Bernard Berthier

    Inventor： Bernard Berthier

    IPC: G06F19/00 ,  G05D1/00 ,  G05D1/08 ,  G05D3/00 ,  B64C39/02 ,  B64C31/036

    CPC classification number: B64C31/036 ,  B64C39/024 ,  B64C2201/105 ,  B64C2201/107

    Abstract: The invention relates to an automatic takeoff method for an aircraft with a flexible airfoil, comprising a carriage suspended by rigging lines from an airfoil. According to said method: —said carriage is provided with an autopilot controlling actuators that control said rigging lines; —said airfoil is provided with an airfoil attitude sensor, comprising a biaxial accelerometer and a biaxial rate gyro, capable of defining the position of an airfoil reference frame in relation to the ground, and means for communicating with said autopilot; —during takeoff, information is received from said airfoil attitude sensor and transmitted to said autopilot for the purpose of controlling said actuators. The invention also relates to an airfoil for the implementation of said method, comprising an airfoil attitude sensor with an inertial unit with a biaxial accelerometer and a biaxial rate gyro, and means for communicating with an autopilot. The invention further relates to an aircraft comprising such an airfoil.

    Abstract translation: 本发明涉及一种具有柔性翼型的飞行器的自动起飞方法，该飞行器包括通过从翼型装配线路悬挂的滑架。 根据所述方法：托架具有控制所述索具线的自动驾驶控制致动器; 翼面设置有翼型姿态传感器，包括双轴加速度计和双轴率陀螺仪，其能够定义相对于地面的翼型参考框架的位置，以及用于与所述自动驾驶仪通信的装置; 在起飞时，为了控制所述致动器，从所述翼型姿态传感器接收信息并传送到所述自动驾驶仪。 本发明还涉及一种用于实现所述方法的翼型件，包括具有带有双轴加速度计和双轴率陀螺仪的​​惯性单元的翼型姿态传感器和用于与自动驾驶仪通信的装置。 本发明还涉及一种包括这种翼型的飞行器。

    ADAPTIVE SOLAR AIRFRAME
    40.
    发明申请
    ADAPTIVE SOLAR AIRFRAME 有权
    自适应太空飞机

    公开(公告)号：US20140203139A1

    公开(公告)日：2014-07-24

    申请号：US14091969

    申请日：2013-11-27

    Applicant: SunLight Photonics Inc.

    Inventor： JOHN PETER MOUSSOURIS ,  SERGEY V. FROLOV ,  MICHAEL CYRUS

    IPC: B64C1/00 ,  B64D3/00

    CPC classification number: B64C1/0009 ,  B64C1/34 ,  B64C3/46 ,  B64C39/024 ,  B64C2201/105 ,  B64D2211/00 ,  G01S3/7861 ,  Y02T50/14

    Abstract: Methods and apparatus for an adaptable solar airframe are provided herein. In some embodiments, an adaptable solar airframe includes an expandable body having an aerodynamic cross-section that reduces parasitic air drag at any given thickness of the body, further being able to change its shape in flight in response to changes in the relative position of the sun; and a flexible solar PV system attached to the surface of the expandable body.

    Abstract translation: 本文提供了适用于太阳能机身的方法和装置。 在一些实施例中，可适应的太阳能机身包括具有空气动力学横截面的可膨胀体，该横截面减小了任何给定厚度的身体的寄生空气阻力，并且还能够响应于相对位置的变化而改变其在飞行中的形状 太阳; 以及附接到可膨胀体表面的柔性太阳能光伏系统。

Patent Agency Ranking