Aircraft weight and center of mass estimation system

    公开(公告)号:US11320333B2

    公开(公告)日:2022-05-03

    申请号:US16927813

    申请日:2020-07-13

    Abstract: A system and various methods for determining a center of mass of an aircraft with a plurality of shock strut assemblies is illustrated. Multiple sensors, including a gas pressure sensor, and/or a position sensor, may be used to gather data and determine the center of mass of the aircraft. Various methods illustrated herein may evaluate the center of mass relative to a wheelbase axis and a wheel tread axis based on the gathered data.

    Electric nose landing gear architecture

    公开(公告)号:US11066153B2

    公开(公告)日:2021-07-20

    申请号:US16592602

    申请日:2019-10-03

    Abstract: A nose landing gear system is disclosed. In various embodiments, the nose landing gear system includes an electro-hydraulic actuator configured to raise and lower a nose shock strut assembly; a first electro-mechanical actuator configured to steer the nose shock strut assembly; and a second electro-mechanical actuator configured to open and close a fairing door.

    DUAL-STAGE, SEPARATED GAS/FLUID SHOCK STRUT SERVICING MONITORING SYSTEM USING TWO PRESSURE/TEMPERATURE SENSORS

    公开(公告)号:US20210027551A1

    公开(公告)日:2021-01-28

    申请号:US17067221

    申请日:2020-10-09

    Abstract: A method for monitoring a dual-stage, separated gas/fluid shock strut includes receiving, by a controller, primary chamber temperature and pressure sensor readings, secondary chamber pressure and temperature sensor readings, and a shock strut stroke sensor reading, determining, by the controller, a shock strut stroke at which a secondary chamber is activated, calculating, by the controller, a volume of oil in an oil chamber of the shock strut, a primary chamber gas volume of, a number of moles of gas in, and a volume of oil leaked into, a primary gas chamber of the shock strut, a secondary chamber gas volume in, a volume of oil leaked into, and a number of moles of gas in, the secondary chamber, based upon at least one of the secondary chamber pressure sensor reading, and the secondary chamber temperature sensor reading.

    Servicing procedure for single-stage mixed fluid/gas shock strut

    公开(公告)号:US10670102B2

    公开(公告)日:2020-06-02

    申请号:US16002917

    申请日:2018-06-07

    Abstract: Methods for servicing shock struts are provided. In various embodiments, a method for servicing a shock strut may comprise deflating the shock strut; compressing the shock strut until the shock strut is in a fully compressed position; and charging the shock strut with a liquid until a pressure of the liquid decreases a volume of a residual air located inside of the shock strut. In various embodiments, charging the shock strut with liquid under pressure may reduce the volume of trapped air inside of the shock strut to a negligible volume, eliminating the servicing variations.

    DUAL-STAGE, STROKE-ACTIVATED, MIXED FLUID GAS SHOCK STRUT SERVICING MONITORING SYSTEM

    公开(公告)号:US20190009892A1

    公开(公告)日:2019-01-10

    申请号:US15642117

    申请日:2017-07-05

    Abstract: A monitoring system for a dual-stage, stroke activated, mixed fluid gas shock strut may comprise a controller, and a tangible, non-transitory memory configured to communicate with the controller. The tangible, non-transitory memory may have instructions stored thereon that, in response to execution by the controller, cause the controller to perform various operations. Said operations may include calculating, by the controller, a compression factor, determining, by the controller, a plurality of compression factors for known oil volumes based on at least one of the primary chamber temperature sensor reading and the shock strut stroke sensor reading, and calculating, by the controller, an oil volume in a primary chamber of the shock strut.

    Hard-landing detection system
    48.
    发明授权

    公开(公告)号:US10112702B2

    公开(公告)日:2018-10-30

    申请号:US15427923

    申请日:2017-02-08

    Abstract: A hard-landing detection system includes a wheel assembly, a shock strut mechanically coupled to the wheel assembly and to landing gear structure of the landing gear assembly, a controller having a processor, and a tangible, non-transitory memory configured to communicate with the processor. The tangible, non-transitory memory has instructions stored thereon that, in response to execution by the processor, cause the hard-landing detection system to perform operations that include detecting, by the processor, a landing event and determining, by the processor, whether the landing event is hard. The hard-landing system may further include a stroke position sensor and detecting the landing event may include using the stroke position sensor to measure a stroke profile of the shock strut. Further, determining whether the landing event is hard may include comparing, by the processor, the stroke profile of the shock strut to a predetermined maximum shock strut stroke.

Patent Agency Ranking