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    ORIENTED WIRE ELECTROSTATIC RADIATION PROTECTION SYSTEM AND METHOD FOR SPACECRAFT
    1.
    发明申请
    ORIENTED WIRE ELECTROSTATIC RADIATION PROTECTION SYSTEM AND METHOD FOR SPACECRAFT 审中-公开

    公开(公告)号：US20200094995A1

    公开(公告)日：2020-03-26

    申请号：US16141933

    申请日：2018-09-25

    Applicant: The Boeing Company

    Inventor： James C. Russell ,  Landon K. Henson

    IPC: B64G1/54

    Abstract: There is provided an oriented wire electrostatic radiation protection system for a spacecraft. The system has a wire management system, and first and second wires coupled to the wire management system. A first wire orientation apparatus orients the first wire in a first wire direction toward, and in parallel alignment with, an approach path of approaching solar particles. A second wire orientation apparatus orients the second wire in a second wire direction opposite to the first wire direction. The system has a control system, and a power supply to charge the first wire to a positively-charged wire and to charge the second wire to a negatively-charged wire. When the approaching solar particles travel alongside the positively-charged wire toward the spacecraft, the positively-charged wire deflects the approaching solar particles away from the spacecraft, via electrostatic repulsion, and the positively-charged wire creates a radiation protection shielded region around the spacecraft.

    Oriented wire electrostatic radiation protection system and method for spacecraft
    3.
    发明授权
    Oriented wire electrostatic radiation protection system and method for spacecraft 有权

    公开(公告)号：US11136147B2

    公开(公告)日：2021-10-05

    申请号：US16141933

    申请日：2018-09-25

    Applicant: The Boeing Company

    Inventor： James C. Russell ,  Landon K. Henson

    IPC: B64G1/54

    Abstract: There is provided an oriented wire electrostatic radiation protection system for a spacecraft. The system has a wire management system, and first and second wires coupled to the wire management system. A first wire orientation apparatus orients the first wire in a first wire direction toward, and in parallel alignment with, an approach path of approaching solar particles. A second wire orientation apparatus orients the second wire in a second wire direction opposite to the first wire direction. The system has a control system, and a power supply to charge the first wire to a positively-charged wire and to charge the second wire to a negatively-charged wire. When the approaching solar particles travel alongside the positively-charged wire toward the spacecraft, the positively-charged wire deflects the approaching solar particles away from the spacecraft, via electrostatic repulsion, and the positively-charged wire creates a radiation protection shielded region around the spacecraft.

    Underwater locator device (ULD) particle suppressor/trap
    5.
    发明授权
    Underwater locator device (ULD) particle suppressor/trap 有权

    公开(公告)号：US11069939B2

    公开(公告)日：2021-07-20

    申请号：US16144443

    申请日：2018-09-27

    Applicant: The Boeing Company

    Inventor： James C. Russell

    IPC: B64D47/06 ,  H01M50/375 ,  B64D45/00 ,  H04B13/02 ,  G01S5/02 ,  G01S5/18 ,  H01M50/35

    Abstract: An avionics unit assembly for an aircraft includes an avionics unit such as an underwater locator device (ULD) having a transmitter configured to output a radio frequency pulse and a battery configured to power the device. The avionics unit assembly can further include a housing that encases the transmitter and the battery and includes a vent port for exhausting an emission from the housing during a failure of the avionics unit. The avionics unit assembly can further include one or more of a suppressor that filters the emission, a shield element that is resistant to chemical and/or thermal effects of the emission, and a bracket for mounting the avionics unit assembly to a surface. The suppressor can include a plurality of channels, where each channel includes at least one blind alley that can capture/filter a particulate component and/or a liquid component from the emission and/or break up the particulate component.

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