An aircraft control position indicator was provided that displayed the degree of deflection of the primary flight control surfaces and the manner in which the aircraft responded. The display included a vertical elevator dot/bar graph meter display for indicating whether the aircraft will pitch up or down, a horizontal aileron dot/bar graph meter display for indicating whether the aircraft will roll to the left or the right, and a horizontal rudder dot/bar graph meter display for indicating whether the aircraft will turn left or right. The vertical and horizontal display or displays intersect to form an up/down, left/right type display. Internal electronic display driver means received signals from transducers measuring the control surface deflections and determined the position of the meter indicators on each dot/bar graph meter display. The device allows readability at a glance, easy visual perception in sunlight or shade, near-zero lag in displaying flight control position, and is not affected by gravitational or centrifugal forces.
Aircraft Control Position Indicator
1984
15 pages
Report
No indication
English
Avionics , Aircraft , Instruments , Patent applications , Aircraft control , Attitude control , Display devices , Flight control , Flight instruments , Position indicators , Visual perception , Centrifugal force , Control surfaces , Deflection , Electronic transducers , Flight characteristics , Pitch (Inclination) , Roll , Yaw
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