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Aircraft control position indicatorAn 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 indication 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 to the right, and a horizontal 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.
Document ID
19870013245
Acquisition Source
Legacy CDMS
Document Type
Other - Patent
Authors
Dennis, Dale V.
(Kentron International, Inc. Hampton, Va., United States)
Date Acquired
August 13, 2013
Publication Date
May 5, 1987
Subject Category
Aircraft Instrumentation
Accession Number
87N22678
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
NASA-CASE-LAR-12984-1|US-PATENT-4,663-627
Patent Application
US-PATENT-APPL-SN-578387
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