Apparatus for sensor failure detection and correction in a gas t

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60 3924, 364431, G05B 1702, F02C 900

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active

042492386

ABSTRACT:
An improved gas turbine engine control system maintains a selected level of engine performance despite the failure or abnormal operation of one or more engine parameter sensors. The control system employs a continuously updated engine model which simulates engine performance and generates signals representing real time estimates of the engine parameter sensor signals. The estimate signals are transmitted to a control computational unit which utilizes them in lieu of the actual engine parameter sensor signals to control the operation of the engine. The estimate signals are also compared with the corresponding actual engine parameter sensor signals and the resulting difference signals are utilized to update the engine model. If a particular difference signal exceeds specific tolerance limits, the difference signal is inhibited from updating the model and a sensor failure indication is provided to the engine operator.

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Montgomery et al.: A Self-Reorganizing Digital Flight Control System for Aircraft, A1AA-12th Aerospace Sciences Meeting, Washington, D.C. 1-30 to 2-1, 1974, pp. 1-13.

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