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    Airfield lighting system
    1.
    发明授权
    Airfield lighting system 失效
    机场照明系统

    公开(公告)号：US5969642A

    公开(公告)日：1999-10-19

    申请号：US722400

    申请日：1996-09-30

    Applicant: Edwin K. Runyon ,  Harold R. Williams ,  Todd E. McCorkle ,  Mark E. Weihs ,  Earl R. Williams

    Inventor： Edwin K. Runyon ,  Harold R. Williams ,  Todd E. McCorkle ,  Mark E. Weihs ,  Earl R. Williams

    IPC: B64F1/18 ,  G08G5/00

    CPC classification number: H05B37/0227 ,  H05B37/0254 ,  B64F1/20 ,  H04B2203/547

    Abstract: A microprocessor-controlled airfield lighting control and monitoring system having bi-directional communication between the controlling microprocessor and the airfield lights and/or sensors. The system also includes a metal container for the remote control microprocessor and an improved attachment arrangement for the power transistor associated therewith. A DC power supply is connected to the remote controller microprocessor and has an integrated circuit adapted to sense a threshold voltage, which causes the power transistor to short around the associated power source.

    Abstract translation: 一种微处理器控制的机场照明控制和监视系统，其在控制微处理器和机场灯和/或传感器之间具有双向通信。 该系统还包括用于遥控微处理器的金属容器和用于与其相关联的功率晶体管的改进的附接装置。 直流电源连接到遥控器微处理器，并且具有适于感测阈值电压的集成电路，这导致功率晶体管围绕相关联的电源短路。

    AXIAL GAP WHEEL MOTOR SUPPORTED BY AUXILIARY BEARINGS IN A SERIES ARRANGEMENT
    3.
    发明申请
    AXIAL GAP WHEEL MOTOR SUPPORTED BY AUXILIARY BEARINGS IN A SERIES ARRANGEMENT 有权

    公开(公告)号：US20250079944A1

    公开(公告)日：2025-03-06

    申请号：US18462085

    申请日：2023-09-06

    Applicant: Kevin R. WILLIAMS

    Inventor： Kevin R. WILLIAMS

    IPC: H02K11/00 ,  B60B27/00 ,  B60K7/00 ,  H02K7/08 ,  H02K7/108 ,  H02K11/33 ,  H02K21/24

    Abstract: A wheel assembly for a vehicle has a rotor housing having permanent magnets therein, a stator support structure having windings therein, and an energy storage module affixed only to said stator support structure. The rotor housing is adapted to be connected to a wheel drive shaft of the vehicle. The rotor housing is adapted to be speed-matched to the rotation of the wheel drive shaft. The windings are spaced from the permanent magnet by an air gap. The stator support structure is supported by a set of auxiliary bearings and is rotatable relative to the rotor housing. The air gap is perpendicular to an axis of rotation of the permanent magnets and the windings. The stator support structure is connected to an outer wheel rim and adapted to rotate as speed-matched to the outer wheel rim. The energy storage module is cooperative with the permanent magnet and the winding so as to receive and transmit energy relative to a motion of the vehicle.

    Condensation resistant power semiconductor module
    4.
    发明授权
    Condensation resistant power semiconductor module 有权

    公开(公告)号：US10959342B2

    公开(公告)日：2021-03-23

    申请号：US16377637

    申请日：2019-04-08

    Applicant: Kevin R. Williams

    Inventor： Kevin R. Williams

    IPC: H05K5/06 ,  H05K5/02 ,  H01L23/50 ,  H01L23/10 ,  H05K7/20 ,  H01L23/367

    Abstract: A power semiconductor module has a base plate, a housing affixed to the base plate, a DC busbar affixed to the base plate and the housing, and AC busbar affixed to the base plate and the housing, control electronics positioned in an interior of the housing and connected to the AC and DC busbars, and a sealant material applied to seams between the base plate in the housing, to seams between the DC busbar and the housing, and to seams between the AC busbar in the housing. The sealant material is applied such that the control electronics of the power semiconductor modules are in an air-tight environment.

    Zero cycle load
    6.
    发明授权
    Zero cycle load 有权

    公开(公告)号：US09996348B2

    公开(公告)日：2018-06-12

    申请号：US13517865

    申请日：2012-06-14

    Applicant: Gerard R. Williams, III ,  John H. Mylius ,  Conrade Blasco-Allue

    Inventor： Gerard R. Williams, III ,  John H. Mylius ,  Conrade Blasco-Allue

    IPC: G06F9/30 ,  G06F9/38

    CPC classification number: G06F9/30043 ,  G06F9/30181 ,  G06F9/3826 ,  G06F9/3834 ,  G06F9/3838 ,  G06F9/384

    Abstract: A system and method for reducing the latency of load operations. A register rename unit within a processor determines whether a decoded load instruction is eligible for conversion to a zero-cycle load operation. If so, control logic assigns a physical register identifier associated with a source operand of an older dependent store instruction to the destination operand of the load instruction. Additionally, the register rename unit marks the load instruction to prevent it from reading data associated with the source operand of the store instruction from memory. Due to the duplicate renaming, this data may be forwarded from a physical register file to instructions that are younger and dependent on the load instruction.

    Pneumatic yaw control effector for aircraft
    7.
    发明授权
    Pneumatic yaw control effector for aircraft 有权

    公开(公告)号：US09944383B2

    公开(公告)日：2018-04-17

    申请号：US15052558

    申请日：2016-02-24

    Applicant: David R. Williams ,  Jürgen Seidel

    Inventor： David R. Williams ,  Jürgen Seidel

    IPC: B64C15/14 ,  B64C39/02 ,  B64D33/00

    CPC classification number: B64C15/14 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/104 ,  B64D33/00

    Abstract: An apparatus and method for controlling a yaw moment of a flight vehicle, such as an aircraft. A wing structure of the flight vehicle has a first opening or actuator positioned by a first apex section of a first side of the wing, and has a second opening or actuator positioned away from or at a distance from a second apex section of a second side of the wing. The first side and the second side can each be positioned or located opposite a centerline of the wing or wing structure. A pressure source or other pressure supply device is in communication with the first opening or actuator and the second opening or actuator to which a pressurized fluid, such as air, is controlled and delivered to control or vary the yaw moment of the flight vehicle.

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