Control apparatus

Registers – Transfer mechanism – Traveling pawl

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Details

235153AE, 318564, G06F 1546, G06F 1108

Patent

active

040327574

ABSTRACT:
Control apparatus for controlling an aircraft gas-turbine engine, having two control lanes operated in parallel with one another and each of which is capable of performing the function of the control apparatus individually, includes a computer and a monitor unit associated with each lane for performing checks on the integrity of the components of both lanes. Transducers in each lane sense engine parameter values and pass signals in accordance therewith to the computer that sends control signals to a control unit and thence to an actuator for adjusting engine variables in accordance with engine-thrust requirements. The control unit includes a pair of cam-operated switches that respond to difference in the values of the control signal from each lane indicative of a fault in the lanes and that trigger operation of the monitor unit in each lane. The monitor units disengage the control signals of the computers from the actuator and cause each computer to pass to the monitors the results of signal comparisons it has made involving signals values of each lane, so that the monitor units can determine in which lane the fault lies. The monitor units reconnect to the actuator control signals from a lane that is found to be operating correctly.

REFERENCES:
patent: 3143693 (1964-08-01), Fearnside et al.
patent: 3476922 (1969-04-01), Yiotis
patent: 3517174 (1970-06-01), Ossfeldt
patent: 3679956 (1972-07-01), Redmond
patent: 3688099 (1972-08-01), Buscher
patent: 3829668 (1974-08-01), Noumi et al.
patent: 3834361 (1974-10-01), Keely
Auricoste et al: Digital Computers Monitor Nuclear Steam Generator, Control Engineering vol. 8; No. 3. Mar. 1961, pp. 127-131.

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