中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

17 records (took 0.012 seconds)

    Methods and Systems for Intelligent Predictive Aircraft Takeoff Rejection Decision Making
    11.
    发明申请
    Methods and Systems for Intelligent Predictive Aircraft Takeoff Rejection Decision Making 审中-公开

    公开(公告)号：US20190049953A1

    公开(公告)日：2019-02-14

    申请号：US15676380

    申请日：2017-08-14

    Applicant: The Boeing Company

    Inventor： Jian Dong ,  Naveed Moayyed Hussain

    IPC: G05D1/00 ,  G08G5/00 ,  G05D1/02

    Abstract: An example method for predictive take-off rejection (TOR) of an aircraft includes receiving, at a computing device on the aircraft and at a time before the aircraft takes off for a current flight, outputs from a plurality of sensors positioned on the aircraft, comparing the outputs received from the plurality of sensors for the current flight to reference flight data, based on comparing the outputs received from the plurality of sensors for the current flight to the reference flight data the computing device making a determination of whether to initiate a TOR procedure before the aircraft reaches a takeoff speed on a runway, and based on determining to initiate the TOR procedure, the computing device sending a signal to a control device on the aircraft to initiate the TOR procedure.

    Fuselage Manufacturing System
    13.
    发明申请
    Fuselage Manufacturing System 有权
    机身制造系统

    公开(公告)号：US20160075451A1

    公开(公告)日：2016-03-17

    申请号：US14717272

    申请日：2015-05-20

    Applicant: The Boeing Company

    Inventor： Jeffrey H. Hunt ,  Naveed Moayyed Hussain

    IPC: B64F5/00 ,  G01S17/89 ,  B21D31/00 ,  G01B11/25

    CPC classification number: B64F5/10 ,  B21B19/02 ,  B21B19/16 ,  B21D31/005 ,  B21D53/92 ,  B23P19/10 ,  B23P2700/01 ,  B64C1/069 ,  G01B11/2518 ,  G01S17/66 ,  G01S17/89

    Abstract: A method and apparatus for processing fuselage sections. A first fuselage section is held in a cradle system. A current shape of the first fuselage section in the cradle system is measured. Forces to change the current shape of the first fuselage section to a desired shape for connecting the first fuselage section to a second fuselage section are identified. The forces identified are applied using a system to change the current shape of the first fuselage section towards the desired shape.

    Abstract translation: 一种用于处理机身部分的方法和装置。 第一个机身部分固定在支架系统中。 测量支架系统中的第一机身部分的当前形状。 识别将第一机身部分的当前形状改变为用于将第一机身部分连接到第二机身部分的期望形状的力。 使用系统来施加所识别的力，以将第一机身部分的当前形状改变为期望的形状。

    Mobile Wiring Harness Anomaly Detection System
    14.
    发明申请
    Mobile Wiring Harness Anomaly Detection System 有权

    公开(公告)号：US20250033795A1

    公开(公告)日：2025-01-30

    申请号：US18494458

    申请日：2023-10-25

    Applicant: The Boeing Company

    Inventor： John Jian Dong ,  Kevin Kuang-Hui Tseng ,  Naveed Moayyed Hussain

    IPC: B64D45/00

    Abstract: An aerospace wiring harness inspection system comprises a mobile personal computing device; a camera system connected to the mobile personal computing device, a machine learning model running in the mobile personal computing device; and a controller. The machine learning model is trained to detect anomalies in a set of images of a wiring harness in an aerospace vehicle. The controller configured to control the camera system to generate a set of images of the wiring harness; send the set of images of the wiring harness to the machine learning model; and receive a result from the machine learning model indicating whether an anomaly is present in the wiring harness.

    MULTI-ROTOR VEHICLE WITH EDGE COMPUTING SYSTEMS
    16.
    发明申请
    MULTI-ROTOR VEHICLE WITH EDGE COMPUTING SYSTEMS 审中-公开

    公开(公告)号：US20200283126A1

    公开(公告)日：2020-09-10

    申请号：US16388374

    申请日：2019-04-18

    Applicant: THE BOEING COMPANY

    Inventor： John Jian Dong ,  Michael James Duffy ,  Douglas C. Cameron ,  Naveed Moayyed Hussain

    IPC: B64C13/24 ,  G05D1/08 ,  B64C39/02 ,  B64C27/32

    Abstract: A multi-rotor vehicle includes a plurality of electric motors and edge computing systems (ECSs). The electric motors are operatively coupled to respective rotors, and cause the respective rotors to rotate relative to the airframe. The ECSs are independent, distinct and distributed to the electric motors, each operatively coupled to a respective electric motor and thereby a respective rotor. Each ECS is configured to acquire and process sensor data for the respective rotor to determine rotor status information, and execute motor commands to control the respective electric motor and thereby the respective rotor. Each ECS is configured as an integrated flight computer and motor controller.

Patent Agency Ranking