中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

61 records (took 0.029 seconds)

    BEAD-STIFFENED MOVABLE SURFACES
    1.
    发明申请
    BEAD-STIFFENED MOVABLE SURFACES 有权

    公开(公告)号：US20220033061A1

    公开(公告)日：2022-02-03

    申请号：US17376140

    申请日：2021-07-14

    Applicant: The Boeing Company

    Inventor： Forouzan Behzadpour ,  Waeil M. Ashmawi ,  Sahrudine Apdalhaliem

    IPC: B64C9/00 ,  B64C3/18 ,  B64C3/26 ,  B64F5/10

    Abstract: A movable surface of an aircraft has a front spar extending along a spanwise direction between opposing movable surface ends. The movable surface also includes a plurality of ribs defining a plurality of bays between adjacent pairs of the ribs. Each rib extends between the front spar and a trailing edge portion of the movable surface. The movable surface further includes an upper and a lower skin panels coupled to the ribs and the front spar. In addition, the bull surface includes a plurality of bead stiffeners coupled to an inner surface of at least one of the upper skin panel and the lower skin panel. The bead stiffeners within the bays are spaced apart from each other and are oriented non-parallel to the front spar and have a bead stiffener cap having opposing cap ends respectively locate proximate the front spar and the trailing edge portion.

    Methods and systems for designing a composite structure
    2.
    发明授权
    Methods and systems for designing a composite structure 有权

    公开(公告)号：US10983078B2

    公开(公告)日：2021-04-20

    申请号：US16691896

    申请日：2019-11-22

    Applicant: The Boeing Company

    Inventor： Sahrudine Apdalhaliem ,  Heh-Chyun Cliff Chen ,  Waeil M. Ashmawi ,  Kimberly D. Meredith

    IPC: G01N25/00 ,  G01N17/00 ,  G01N33/44 ,  B64F5/60 ,  G01N5/02

    Abstract: A computer-implemented method of determining moisture content of a composite structure is provided. The method includes performing a thermal analysis calculation on the composite structure to determine a temporal surface temperature profile of the composite structure based on temporal environmental parameter profiles, wherein the surface temperature profile is determined independently of a moisture content of the composite structure. The method also includes performing a moisture content analysis calculation on the composite structure to determine a moisture content of the composite structure, wherein the moisture content analysis calculation is based on the determined temporal surface temperature profile and a thickness of the composite structure. The thermal analysis calculation is performed iteratively with a first time period and the moisture content analysis calculation is performed iteratively with a second time period that is longer than the first time period.

    SYSTEM AND METHOD FOR HARVESTING ENERGY FROM A MOVING VEHICLE
    4.
    发明申请
    SYSTEM AND METHOD FOR HARVESTING ENERGY FROM A MOVING VEHICLE 审中-公开

    公开(公告)号：US20170194881A1

    公开(公告)日：2017-07-06

    申请号：US14987115

    申请日：2016-01-04

    Applicant: The Boeing Company

    Inventor： Sahrudine Apdalhaliem ,  Waeil M. Ashmawi

    IPC: H02N2/18 ,  H02J7/00 ,  B64C3/18 ,  B60R16/03

    CPC classification number: H02N2/18 ,  B60R16/03 ,  B64C3/185 ,  B64C3/187 ,  B64D41/00 ,  F16B5/02 ,  H02J7/0052 ,  Y02T50/44 ,  Y02T50/53

    Abstract: A system and method for harvesting energy from a vehicle, e.g., an aircraft, in operation. A plurality of piezoelectric members are coupled between structural members in the vehicle. A first portion of the plurality of piezoelectric members are non-resonant piezoelectric spacers coupled between structural members subject to a constant load during operation of the vehicle. A second portion of the plurality of piezoelectric members are resonant piezoelectric fillers coupled between structural members subject to a cyclical load during operation of the vehicle. Electrical conversion circuitry is coupled to each of the plurality of piezoelectric members for converting the output of each piezoelectric member to usable electrical energy. The electrical conversion circuitry is coupled to an energy storage device for storing the usable electrical energy and/or to an interface circuit for supplying energy for use in an electrical system in the vehicle.

    Water and ice detection and quantitative assessment system for ingression prone areas in an aircraft
    5.
    发明授权
    Water and ice detection and quantitative assessment system for ingression prone areas in an aircraft 有权
    航空器入侵倾向区域的水和冰检测和定量评估系统

    公开(公告)号：US09546004B1

    公开(公告)日：2017-01-17

    申请号：US14216397

    申请日：2014-03-17

    Applicant: The Boeing Company

    Inventor： Morteza Safai ,  Kimberly D. Meredith ,  Sahrudine Apdalhaliem

    IPC: B64D45/00 ,  G01N27/02

    CPC classification number: B64D45/00 ,  B64C1/067 ,  B64D13/06 ,  B64D2013/0662 ,  G01N27/02 ,  Y02T50/56

    Abstract: A water and ice detection and quantitative assessment system (“WIDQAS”) for moisture detection and assessment of water accumulation on an aircraft having an airframe that has at least one enclosed space within the airframe is described. The WIDQAS may include a plurality of sensors and a data measurement device. The plurality of sensors may be arranged in the at least one enclosed space within the airframe and each sensor of the plurality of sensors may be configured to detect a presence of moisture in the at least one enclosed space and generate a data measurement that is responsive to the detection of moisture in the at least one enclosed space. The data measurement device is in signal communication with the plurality of sensors and may be configured to record the data measurement for each sensor and record identifying information about the measurement during a flight of the aircraft.

    Abstract translation: 描述了用于水分检测和评估具有在机身内具有至少一个封闭空间的机身的飞机上的积水的水和冰检测和定量评估系统（“WIDQAS”）。 WIDQAS可以包括多个传感器和数据测量装置。 多个传感器可以布置在机身内的至少一个封闭空间中，并且多个传感器中的每个传感器可被配置为检测至少一个封闭空间中的湿气的存在并产生响应于 检测所述至少一个封闭空间中的水分。 所述数据测量装置与所述多个传感器进行信号通信，并且可以被配置为记录每个传感器的数据测量，并在飞行器飞行期间记录关于测量的识别信息。

    SMART SUSCEPTOR FOR A SHAPE MEMORY ALLOY (SMA) ACTUATOR INDUCTIVE HEATING SYSTEM
    10.
    发明申请
    SMART SUSCEPTOR FOR A SHAPE MEMORY ALLOY (SMA) ACTUATOR INDUCTIVE HEATING SYSTEM 有权
    形状记忆合金（SMA）执行器感应加热系统的智能断路器

    公开(公告)号：US20150096293A1

    公开(公告)日：2015-04-09

    申请号：US14045121

    申请日：2013-10-03

    Applicant: The Boeing Company

    Inventor： Moushumi Shome ,  Frederick T. Calkins ,  Stephen R. Amorosi ,  Flint M. Jamison ,  Sahrudine Apdalhaliem ,  Robert James Miller

    IPC: F03G7/06 ,  H01F41/02

    CPC classification number: F03G7/065 ,  H01F41/02 ,  Y10T29/4902

    Abstract: A system for heating a shape memory alloy (SMA) actuator may include an SMA actuator, a smart susceptor, a plurality of induction coils, and a control module. The SMA actuator may have at least one layup. The SMA actuator may be selectively heated to a transition temperature. The smart susceptor may be in thermal contact with the at least one layup of the SMA actuator. The induction heating coils may be configured to receive an alternating current and generate a magnetic field based on the alternating current. The magnetic field may create an eddy current in at least one of the SMA actuator and the smart susceptor to heat the SMA actuator to the transition temperature. The control module may be configured to drive the alternating current supplied to the induction heating coils.

    Abstract translation: 用于加热形状记忆合金（SMA）致动器的系统可以包括SMA致动器，智能基座，多个感应线圈和控制模块。 SMA致动器可以具有至少一个叠层。 可以将SMA致动器选择性地加热到转变温度。 智能基座可以与SMA致动器的至少一个叠层热接触。 感应加热线圈可以被配置为接收交流电流并且基于交流电产生磁场。 磁场可以在SMA致动器和智能基座中的至少一个中产生涡流，以将SMA致动器加热到转变温度。 控制模块可以被配置为驱动提供给感应加热线圈的交流电。

Patent Agency Ranking