Patent ID: 8886402
Filing Date: 2014-11-11
Classification: B64C,F16F,G01C,G01M

Abstract:
1. A system for actively controlling the load response characteristics of a shock absorbing aircraft landing gear assembly, comprising: a shock absorbing strut disposed between a displaceable, ground contacting portion of the landing gear assembly and the airframe of the aircraft; a passage from a first fluid chamber in the strut to a second fluid chamber in the strut; a controllable valve adapted for actively varying a load response characteristic of the shock absorbing strut by controlling the rate at which fluid may flow through the passage from the first fluid chamber to the second fluid chamber; a sensor onboard the aircraft providing a signal representative of an aircraft landing parameter; and a control system comprising an input for receiving the sensor signal, an algorithm adapted to calculate the rate at which the aircraft is closing with the ground using sink rate and height above ground data, and determine an associated optimal position for the controllable valve, and an output for sending a control signal to the controllable valve to place the valve in the optimal position prior to the aircraft touching down.