中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

295 records (took 0.013 seconds)

    Anti-submarine warfare UAV and method of use thereof
    231.
    发明授权
    Anti-submarine warfare UAV and method of use thereof 失效
    反潜战无人机及其使用方法

    公开(公告)号：US06409122B1

    公开(公告)日：2002-06-25

    申请号：US09761076

    申请日：2001-01-17

    Applicant: Leland M. Nicolai

    Inventor： Leland M. Nicolai

    IPC: B64C3500

    CPC classification number: B64C35/005 ,  B60V1/08 ,  B64C39/024 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/167 ,  B64C2201/187

    Abstract: An anti-submarine warfare system includes an unmanned “sea-sitting” aircraft housing submarine detecting equipment, the aircraft including a body portion having a catamaran configuration adapted for stably supporting the body portion when sitting in water, the body portion including a fuselage and laterally disposed sponsons connected to the fuselage via platforms, and submarine detecting equipment housed within the fuselage and adapted to be electronically linked to sonobuoys disposed in adjacent water locations.

    Abstract translation: 一种反潜战系统包括一个无人“海坐”飞机舱潜艇检测设备，该飞机包括一个主体部分，该主体部分具有适于在坐在水中时稳定地支撑主体部分的双体船结构，该主体部分包括机身和横向 通过平台连接到机身的安装支架，以及容纳在机身内的潜艇检测设备，并且适于与设置在相邻水位的声波电子电子连接。

    High-G compact folding wing
    232.
    发明授权
    High-G compact folding wing 失效
    高G小型折叠翼

    公开(公告)号：US06260798B1

    公开(公告)日：2001-07-17

    申请号：US09425609

    申请日：1999-10-22

    Applicant: Thierry Casiez ,  Carlos Cesnik ,  Mark Drela ,  Staci N. Jenkins ,  Mark Spearing

    Inventor： Thierry Casiez ,  Carlos Cesnik ,  Mark Drela ,  Staci N. Jenkins ,  Mark Spearing

    IPC: B64C338

    CPC classification number: B64F1/04 ,  B64C3/56 ,  B64C39/024 ,  B64C2201/102 ,  Y02T50/14

    Abstract: A compact, aerodynamic wing assembly constructed and arranged so as to withstand a force due to acceleration in at least one direction includes at least two wing segments, each of the wing segments having a span-wise axis, and a airfoil cross section normal to the span axis. The wing segments are preferably disposed mutually adjacent and end to end. For each pair of wing segments, the wing further includes a pivot assembly fixedly attached to the wing segments at an end of each of the wing segments along the span-wise axis. The pivot assembly forms an articulation axis for relative movement between each the pair of wing segments, such that the wing assembly converts, upon a predetermined stimulus, from a stowed configuration characterized by nested wing segments, to a deployed configuration characterized by a substantially uninterrupted aerodynamic surface. The wing assembly is preferably constructed and arranged to withstand forces due to acceleration in at least two directions, including 15,000 g's forward and 4,000 g's rebound accelerations. The invention further comprises a flying structure constructed and arranged so as to withstand an acceleration force directed along a main axis. The flying structure includes a body disposed about the main axis, and at least one wing assembly pivotally mounted to the body. The wing assembly is constructed and arranged so as to convert, upon a predetermined stimulus, from a stowed configuration characterized by nested wing segments, to a deployed configuration characterized by a substantially uninterrupted aerodynamic surface.

    Abstract translation: 构造和布置为承受由于至少一个方向上的加速度而产生的力的紧凑的空气动力学翼组件包括至少两个翼段，每个翼段具有跨度轴线，并且翼型横截面垂直于 跨度轴。 翼片段优选地彼此相邻并且端对端设置。 对于每对翼段，机翼还包括枢转组件，该枢轴组件沿翼展轴线固定地连接到每个翼片段的端部处的翼段。 枢轴组件形成用于每对翼段之间的相对运动的铰接轴线，使得翼组件在预定的刺激下将由嵌套的翼片段特征的收起构型转换成展开的构型，其特征在于基本上不间断的空气动力学 表面。 翼组件优选地构造和布置成承受由于至少两个方向上的加速的力，包括15,000g的向前和4,000g的回弹加速度。 本发明还包括一个构造和布置以便承受沿主轴定向的加速力的飞行结构。 飞行结构包括围绕主轴设置的主体，以及枢转地安装到主体的至少一个翼组件。 机翼组件被构造和布置成在预定的刺激下从由特征为嵌套的翼段的收起构型转换到特征在于基本上不间断的空气动力学表面的展开构型。

    FOLDABLE WINGS FOR AN UNMANNED AERIAL VEHICLE
    235.
    发明申请
    FOLDABLE WINGS FOR AN UNMANNED AERIAL VEHICLE 审中-公开

    公开(公告)号：US20190023374A1

    公开(公告)日：2019-01-24

    申请号：US15755669

    申请日：2016-08-25

    Applicant: UVISION AIR LTD

    Inventor： MOSHE KAHLON ,  AMIT MORAG

    IPC: B64C3/56 ,  B64C39/02

    CPC classification number: B64C3/56 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/08 ,  B64C2201/102 ,  B64C2201/201 ,  B64C2201/203 ,  F42B10/14

    Abstract: An unmanned air vehicle (UAV) having a fuselage, a foldable propulsion means to generate thrust leading to the UAV movement, a driving means to drive the propulsion means and a plurality of flight control surfaces actuators are further included. The UAV further includes at least one pair of foldable wings where the rear portion of the wings is pivotally attached to the fuselage. The wings having at least one roll control surface hinged to at least one of the foldable wings. At least a pair of tail stabilizers having ruddervators flight control surfaces hinged to the tail stabilizers. In a fully extended position or in ready to fly state position, each of the foldable wings are deployed perpendicular to one another and perpendicular to the fuselage to form an offset-x shaped wings, and in a stowed position, each of the wings are positioned parallel to one another and positioned parallel to the fuselage.

    DEPLOYABLE AIRFOIL AIRBORNE BODY AND METHOD OF SIMULTANEOUS TRANSLATION AND ROTATION TO DEPLOY
    236.
    发明申请
    DEPLOYABLE AIRFOIL AIRBORNE BODY AND METHOD OF SIMULTANEOUS TRANSLATION AND ROTATION TO DEPLOY 审中-公开

    公开(公告)号：US20180372464A1

    公开(公告)日：2018-12-27

    申请号：US15634530

    申请日：2017-06-27

    Applicant: Raytheon Company

    Inventor： Joseph P. Dylla ,  Michael J. Scolman

    IPC: F42B10/14 ,  B64C39/02

    CPC classification number: F42B10/14 ,  B64C39/024 ,  B64C2201/102

    Abstract: A deployable airfoil airborne body such as missiles, bombs, guided projectiles, MALDs and UAVs includes first and second rigid airfoil sections stowed end-to-end along the airborne body. The airfoil sections have first and second interior edges of equal lengths, abutting ends connected at the first and second interior edges by a free-floating pivot, a distant end of the first rigid airfoil section coupled to a fixed pivot on the airborne body, and a distant end of the second rigid airfoil section having a translation point. The first and second rigid airfoil sections are configured to rotate in opposite directions to move the translation point axially along the airborne body to abut the fixed pivot driving the free-floating pivot radially away from the airborne body to join the first and second interior edges in a deployed position transverse to the airborne body to form a rigid airfoil

Patent Agency Ranking