Aircraft pitch-axis stability and command augmentation system
Number of patents in Portfolio can not be more than 2000
United States of America Patent
Stats
-
Dec 4, 2001
Issued Date -
N/A
app pub date -
Jul 20, 2000
filing date -
May 15, 1995
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
A bias correction system for use in a neutrally-stable aircraft having a control column and a pitch control system is provided. The position of the control column is generally represented by a control column position signal. The bias correction system is for removing control column bias when the control column is in a neutral position. The bias correction system includes a first combining unit for combining the control column position signal and a correction signal, and a switch. The switch includes activated and deactivated states. The switch is set to the deactivated state when the control column is physically displaced from its neutral position. The deactivated state allows the correction signal to remain at its last value, the activated state allows the correction signal to equal approximately the control column position signal. In one embodiment, the bias correction system includes a smoothing filter for receiving the control column position signal and outputting a smoothed correction signal when the switch is in the activated state. In another embodiment, the bias correction system includes a unit for limiting the correction signal to control column position signal values within a limited predefined range.
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