This utility model discloses an airship
control system based on an execution drive
encoder board, comprising a flight control computer, an execution drive
encoder board, a
logic control circuit, and output ports. The flight control computer can output six control signals (PWM0-PWM5). The execution drive
encoder board integrates six 2-to-1 analog switches, with the switch inputs connected to the six
PWM signals output from the flight control computer and the execution drive board, respectively. The
logic control circuit consists of OR gates, XOR gates, and AND gates, with its inputs connected to the control terminals of each analog switch, receiving control authority feedback signals from the execution drive board and control status feedback signals from the flight control computer. The output ports output the six
PWM signals selected by the analog switches, respectively driving the servos corresponding to the horizontal
tail, vertical
tail, duct tilt, duct lock, engine
throttle, and engine shutdown. This solution addresses the problems of insufficient
control signal switching flexibility, incomplete
control logic, and poor
system scalability in existing airship control systems.