eVTOL Fly-By-Wire Voting Control for Fault-Tolerant Thrust
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Solution Overview
Problem
In electric aircraft, particularly eVTOLs, there is a need for reliable fly-by-wire flight control systems to ensure safety by accurately assessing and adjusting propulsor output to maintain aircraft integrity and maneuverability, especially in case of component malfunctions.
Innovation Solution
A fly-by-wire flight control system that includes a flight controller performing a voting algorithm to validate sensor data, determining admissible commands, and generating electrical signals for control surface movement, with actuators adjusting propulsor thrust accordingly, ensuring safe and stable aircraft operations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a voting algorithm is implemented to validate sensor data and filter faulty inputs, then the reliability of flight control is improved, but the device complexity increases due to additional processing requirements
Solution Approach 1:
The voting algorithm implements feedback by continuously monitoring sensor data from multiple sources, comparing readings, and using the consensus value to control flight surfaces. This feedback mechanism ensures that faulty sensor inputs are detected and corrected through comparison with other sensors, maintaining reliable flight control while using established control theory principles
Solution Approach 2:
The system segments the sensor validation function into discrete voting algorithms that process data from individual sensors independently. Each sensor reading is evaluated separately through the voting process, allowing the system to identify and exclude faulty individual sensors while maintaining overall system reliability without requiring complete system redesign
2Reliability
If multiple sensors and voting algorithms are used to ensure safe operation, then the reliability improves, but the loss of time increases due to additional data processing steps
Solution Approach 1:
The voting algorithm performs preliminary validation of sensor data by continuously comparing readings from multiple sensors before critical failures occur. This preliminary action establishes baseline expectations for sensor behavior and pre-computes voting logic, enabling rapid response when discrepancies are detected without requiring time-consuming analysis during emergency situations
Solution Approach 2:
The system changes the parameter of data validation from checking single sensor readings to evaluating multiple sensor parameters simultaneously through voting. By processing multiple parameters in parallel through the voting algorithm, the system achieves thorough validation while maintaining response times suitable for flight control applications
3Stability of the object's composition
If the system continuously monitors and adjusts propulsor thrust to maintain aircraft integrity, then the stability improves, but the use of energy increases
Solution Approach 1:
The flight control system performs self-service by automatically monitoring sensor data, executing voting algorithms, and adjusting propulsor thrust without requiring continuous pilot intervention. This self-regulating mechanism maintains aircraft stability autonomously, reducing the need for manual corrections and optimizing energy usage by making adjustments only when necessary to maintain safe operation
Data Source
AI summary
In an aspect a system for fly-by-wire flight control configured for use in electric aircraft including at least a sensor, wherein the sensor is communicatively connected a pilot control and configured to detect a pilot input from the pilot control and generate, as a function of the pilot input, command datum. A system includes a flight controller, the flight controller including a computing device and configured to perform a voting algorithm, wherein performing the voting algorithm includes determining that the sensor is an allowed sensor, wherein determining that the sensor is an allowed sensor includes determining that the command datum is an active datum, determining the command datum is an admissible datum, generating, as a function of the command datum and the allowed sensor, a control surface datum wherein the control surface datum is correlated to the pilot input.