Aircraft hybrid duplex-triplex control architecture
Aircraft control architectures include a triplex sensor configured to output three signals. First and second channels are configured to receive respective signals of the three output signals, with each channel having a respective processor and are configured to output respective control signals. A remote interface device is configured to receive a third signal of the three output signals and an effector is configured to receive the first and second control signals and perform an action in response to the control signals. An output from the remote interface device is transmitted to the first and second channels and an output from each channel is received at the other channel. The control signals are based on the received signals, the received outputs from the remote interface device, and the received output from the other channel.
1. An aircraft control architecture comprising:
a triplex sensor configured to output three signals;
a first channel configured to receive a first signal of the three output signals, the first channel comprising a first processor and output a first control signal;
a second channel configured to receive a second signal of the three output signals, the second channel comprising a second processor and output a second control signal;
a remote interface device configured to receive a third signal of the three output signals; and
an effector configured to receive the first control signal and the second control signal and configured to perform an action in response to the first control signal and the second control signal,
wherein an output from the remote interface device is transmitted to each of the first channel and the second channel,
wherein an output from the first channel is received at the second channel and an output from the second channel is received at the first channel,
wherein the first control signal is based on the first signal, the output from the remote interface device, and the output from the second channel, and
wherein the second control signal is based on the second signal, the output from the remote interface device, and the output from the first channel.
2. The aircraft control architecture of claim 1 , wherein the effector is a duplex effector.
3. The aircraft control architecture of claim 1 , where at least one of the first channel and the second channel comprise:
an analog-to-digital converter for receiving an analog signal from the triplex sensor and generating a digital signal;
a digital circuit for processing the digital signal;
a digital-to-analog converter for outputting an analog signal to the effector based on the processed digital signal;
a processor for controlling operation of the digital circuit to generate the processed digital signal; and
a power supply configured to supply power to at least the processor.
4. The aircraft control architecture of claim 1 , wherein the remote interface device comprises:
an analog-to-digital converter for receiving an analog signal from the triplex sensor and generating a digital signal;
a digital circuit for processing the digital signal;
a digital-to-analog converter for outputting an analog signal to the effector based on the processed digital signal; and
a programmable array configured to store instructions for the digital circuit to generate the digital signal.
5. The aircraft control architecture of claim 1 , wherein the effector is a triplex effector.
6. The aircraft control architecture of claim 5 , wherein the triplex effector receives as an input an output from the remote interface device.
7. The aircraft control architecture of claim 5 , wherein the remote interface device is a first remote interface device, the aircraft control architecture further comprising:
a second remote interface device configured to receive as an input an output from the first channel and the second channel and output a signal to be sent to the triplex effector.
8. The aircraft control architecture of claim 1 , wherein the triplex sensor comprises at least one of a temperature sensor, a pressure sensor, a strain gauge, a speed sensor, an accelerometer, or a lube sensor.
9. The aircraft control architecture of claim 1 , wherein the effector is at least one of a motor, an actuator, a solenoid, a valve, a relay, a pump, or a heater.
10. An aircraft comprising:
an engine; and
an aircraft control architecture configured to control operation of the engine, the aircraft control architecture comprising:
a triplex sensor configured to output three signals;
a first channel configured to receive a first signal of the three output signals, the first channel comprising a first processor and output a first control signal;
a second channel configured to receive a second signal of the three output signals, the second channel comprising a second processor and output a second control signal;
a remote interface device configured to receive a third signal of the three output signals; and
an effector configured to receive the first control signal and the second control signal and configured to perform an action in response to the first control signal and the second control signal,
wherein an output from the remote interface device is transmitted to each of the first channel and the second channel,
wherein an output from the first channel is received at the second channel and an output from the second channel is received at the first channel,
wherein the first control signal is based on the first signal, the output from the remote interface device, and the output from the second channel, and
wherein the second control signal is based on the second signal, the output from the remote interface device, and the output from the first channel.
11. The aircraft of claim 10 , wherein the effector is a duplex effector.
12. The aircraft of claim 10 , where at least one of the first channel and the second channel comprise:
an analog-to-digital converter for receiving an analog signal from the triplex sensor and generating a digital signal;
a digital circuit for processing the digital signal;
a digital-to-analog converter for outputting an analog signal to the effector based on the processed digital signal;
a processor for controlling operation of the digital circuit to generate the processed digital signal; and
a power supply configured to supply power to at least the processor.
13. The aircraft of claim 10 , wherein the remote interface device comprises:
an analog-to-digital converter for receiving an analog signal from the triplex sensor and generating a digital signal;
a digital circuit for processing the digital signal;
a digital-to-analog converter for outputting an analog signal to the effector based on the processed digital signal; and
a programmable array configured to store instructions for the digital circuit to generate the digital signal.
14. The aircraft of claim 10 , wherein the effector is a triplex effector.
15. The aircraft of claim 14 , wherein the triplex effector receives as an input an output from the remote interface device.
16. The aircraft of claim 14 , wherein the remote interface device is a first remote interface device, the aircraft control architecture further comprising:
a second remote interface device configured to receive as an input an output from the first channel and the second channel and output a signal to be sent to the triplex effector.
17. The aircraft of claim 10 , wherein the triplex sensor comprises at least one of a temperature sensor, a pressure sensor, a strain gauge, a speed sensor, an accelerometer, or a lube sensor.
18. The aircraft of claim 10 , wherein the effector is at least one of a motor, an actuator, a solenoid, a valve, a relay, a pump, or a heater.
19. The aircraft of claim 10 , wherein the aircraft is configured to be operated by a single pilot.