Distributed Aircraft Pilot Control for Common-Mode Failure Resistance
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Solution Overview
Problem
Modern aircraft rely on centralized flight control computers that are prone to common mode failures, which can lead to catastrophic failures in fly-by-wire systems, as these systems are susceptible to single points of failure and require robust distributed control solutions to ensure safe operation.
Innovation Solution
A distributed pilot control system is implemented, comprising multiple flight components and aircraft components that receive commands from sensors and attitude sensors, allowing for decentralized decision-making and response generation to ensure continued flight safety in case of failures.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a centralized flight control computer is used, then the control system is simpler to implement, but the system becomes susceptible to common mode failures and single points of failure
Solution Approach 1:
The patent divides the centralized flight control computer into multiple distributed flight control computers (first, second, third FCUs). Each FCU independently controls specific flight components, eliminating single points of failure. The segmentation allows the system to maintain functionality even when individual components fail, directly resolving the contradiction between structural simplicity and failure resistance.
2Reliability
If multiple distributed flight components are used, then the reliability and safety are improved, but the device complexity increases
Solution Approach 1:
The patent implements universal communication protocols and standardized interfaces among all distributed flight control computers and flight components. This multi-functionality approach allows different FCUs to interchangeably control various flight components, reducing the complexity burden of distribution while maintaining high reliability through redundancy and failover capabilities.
Data Source
AI summary
A system for a distributed pilot control of an aircraft is disclosed. The system includes a plurality of flight components. The system also includes an aircraft control located within the aircraft. The system includes an aircraft component attached to a flight component of the plurality of flight components. The aircraft component is configured to receive, from a command sensor attached to the aircraft control, an aircraft command. The aircraft component is configured to obtain, from an attitude sensor, an aircraft orientation. The aircraft component is configured to receive, as a function of a notification unit, a pilot signal. The aircraft component is additionally configured to command the flight component to produce a response command as a function of the pilot signal.