(57) ABSTRACT A monitoring system for a dual-stage, separated gas/fluid shock strut may
comprise a controller and a tangible, non transitory memory configured to communicate with …

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 …

(74) Attorney, Agent, or Firm—Snell & Wilmer LLP (57) ABSTRACT A monitoring system for
a dual-stage, stroke activated, mixed fluid gas shock strut may comprise a controller, and a …

(57) ABSTRACT A monitoring system for a dual-stage, pressure-activated, mixed fluid gas
shock strut, may comprise a controller, and a tangible, non-transitory memory configured to …

An aircraft landing gear assembly having a main strut configured to move between a
deployed condition and a stowed condition, a damping device to oppose movement of the …

(57) ABSTRACT A monitoring system for a dual-stage, separated gas/fluid shock strut may
comprise a controller and a tangible, non transitory memory configured to communicate with …

A method includes detecting at least one position measurement of a separator piston of a
pitch trim actuator. The method includes detecting at least one pressure measurement of an …

A method for monitoring a dual-stage, stroke activated, mixed fluid gas shock strut includes
receiving, by a controller, primary chamber temperature and pressure sensor readings …

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 …

A method for monitoring a dual-stage, separated gas/fluid shock strut includes receiving, by
a controller, a primary chamber temperature sensor reading, a primary chamber pressure …