Aircraft Electric Motor Cutoff for Uncommanded Torque Prevention
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Solution Overview
Problem
Existing control systems for hybrid-electric propulsion systems in aircraft are prone to uncommanded rapid torque acceleration due to control system failures, posing a risk during critical flight conditions like landing sequences.
Innovation Solution
A control unit or battery management system monitors power lever angles and electrical current thresholds to disable the electric motor by deenergizing or electrically isolating it when conditions exceed predefined thresholds, preventing uncommanded torque acceleration.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If the electric motor is enabled to provide propulsion power, then the aircraft propulsion capability is improved, but the risk of uncommanded rapid torque acceleration increases due to control system failures
Solution Approach 1:
The control system is configured to detect control system failures and automatically disable the electric motor before uncommanded torque acceleration can occur. This preliminary protective action prevents the harmful effect while maintaining normal operation during healthy conditions.
Solution Approach 2:
A control system acts as an intermediary between the electric motor and the propulsion system, monitoring system health and intervening to disable the motor when failures are detected, thereby preventing uncommanded torque acceleration while allowing full power operation during normal conditions.
2Reliability
If the electric motor is disabled through deenergizing or electrical isolation, then the safety against uncommanded torque acceleration is improved, but the response time and operational flexibility are reduced
Solution Approach 1:
The control system performs preliminary detection of control system failures and automatically executes motor disablement before uncommanded torque acceleration can occur, ensuring safety while minimizing response time through automated real-time monitoring and immediate protective action.
Data Source
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AI summary
A propulsion system (20) for an aircraft (1000) includes a propulsor (28), an engine (22), an electrical assembly (24), and a control unit (82). The engine (22) includes a rotational assembly (44, 46). The rotational assembly (44, 46) is coupled to the propulsor (28). The electrical assembly (24) includes an electric motor (62), an electrical distribution system (66), and an electrical current sensor (80). The electric motor (62) is coupled to the propulsor (28). The electric motor (62) is electrically connected to the electrical distribution system (66). The electrical current sensor (80) is configured to measure an electrical current supplied to the electric motor (62) by the electrical distribution system (66). The control unit (82) is configured to identify a power lever angle (1006) of a power throttle (1004) for the propulsion system (20) is greater than or less than a power threshold, identify the electrical current is greater than or less than an electrical current threshold in response to identifying the power lever angle (1006) is less than the power threshold, and disable the electric motor (62) in response to identifying the electrical current is greater than the electrical current threshold.