Accession Number : AD0480391
Title : INVESTIGATION AND APPLICATION OF ELEMENT REDUNDANCY IN FLIGHT CONTROL SYSTEM SENSORS.
Descriptive Note : Final rept. Jan 65-Mar 66,
Corporate Author : GENERAL ELECTRIC CO JOHNSON CITY NY LIGHT MILITARY ELECTRONICS DEPT
Personal Author(s) : Danyluk, P. R. ; Hogan, D.
Report Date : MAR 1966
Pagination or Media Count : 43
Abstract : The objective of this program was to investigate means by which the reliability of flight control stability augmentation sensors could be improved by the use of redundancy, preferably at an elemental level. The investigation did not uncover any approach involving redundant elements that promised a significant reliability improvement. Rate gyro failures, as opposed to catastrophic failures, are largely of a drift nature. The use of suspension spring stress rather than gimbal position as an output is suggested as a means of reducing null shift errors. Further, sensors should be applied in redundant sets and the median signal selected by means of any of several voter circuits to accomplish that end. A production rate gyro was modified to include semiconductor strain gages on the suspension spring. Evaluation data taken on this gyro and recommended design features for a new gyro are included. (Author)
Descriptors : (*FLIGHT CONTROL SYSTEMS, RELIABILITY), GYROSCOPES, FAILURE(MECHANICS), ACCELEROMETERS, DEFECTS(MATERIALS), SEMICONDUCTOR DEVICES, STRAIN GAGES, REDUNDANT COMPONENTS.
Subject Categories : Aircraft
Distribution Statement : APPROVED FOR PUBLIC RELEASE