The redundancy control device includes three controllers that output status signals, a majority voting circuit to which a first voltage or a second voltage is supplied as an output signal through an output line of each controller, a switch provided in each output line, a voltage supply unit provided for each output line to supply the second voltage to the output line when the first voltage is lost, a latch circuit provided for each output line to latch the second voltage when the second voltage is supplied thereto and continue to output the second voltage, a comparison circuit provided for each controller to output a comparison signal based on a comparison of the status signals, and a switch control unit provided for each switch to outputs a switch signal to the switch in response to the comparison signal from the comparison circuit.
REDUNDANCY CONTROL DEVICE FOR AIRCRAFT
2021-09-09
Patent
Electronic Resource
English
Computer redundancy for aircraft flight control
AIAA | 1977
|Computer redundancy for aircraft flight control
Tema Archive | 1977
|Aircraft control method and device based on dual-redundancy bus and aircraft
European Patent Office | 2022
|