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digital fly-by-wire flight control validation experienceThe experience gained in digital fly-by-wire technology through a flight test program being conducted by the NASA Dryden Flight Research Center in an F-8C aircraft is described. The system requirements are outlined, along with the requirements for flight qualification. The system is described, including the hardware components, the aircraft installation, and the system operation. The flight qualification experience is emphasized. The qualification process included the theoretical validation of the basic design, laboratory testing of the hardware and software elements, systems level testing, and flight testing. The most productive testing was performed on an iron bird aircraft, which used the actual electronic and hydraulic hardware and a simulation of the F-8 characteristics to provide the flight environment. The iron bird was used for sensor and system redundancy management testing, failure modes and effects testing, and stress testing in many cases with the pilot in the loop. The flight test program confirmed the quality of the validation process by achieving 50 flights without a known undetected failure and with no false alarms.
Document ID
19790005938
Document Type
Technical Memorandum (TM)
Authors
Szalai, K. J.
(NASA Hugh L. Dryden Flight Research Center Edwards, CA, United States)
Jarvis, C. R.
(NASA Hugh L. Dryden Flight Research Center Edwards, CA, United States)
Krier, G. E.
(NASA Hugh L. Dryden Flight Research Center Edwards, CA, United States)
Megna, V. A.
(Charles Stark Draper Lab. Inc.,, United States)
Brock, L. D.
(Charles Stark Draper Lab. Inc.,, United States)
Odonnell, R. N.
(Charles Stark Draper Lab. Inc.,, United States)
Date Acquired
September 3, 2013
Publication Date
December 1, 1978
Subject Category
AIRCRAFT STABILITY AND CONTROL
Report/Patent Number
R-1164
NASA-TM-72860
H-1080
Funding Number(s)
PROJECT: RTOP 512-51-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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