Electric Motor Decoupling for Hybrid Aircraft Fault Isolation
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Solution Overview
Problem
Current aircraft propulsion systems lack effective means to isolate electric motors from the propulsion system during faults, which can impact engine and aircraft system safety and efficiency.
Innovation Solution
A power management system incorporating a controller with a memory device and processor, a propeller control for adjusting pitch angle, and a disconnect switch to mechanically decouple the electric motor from the propulsion system, providing two independent isolation paths to mitigate fault conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If electric motor is integrated into aircraft propulsion system, then propulsive efficiency and performance are improved, but system complexity and fault contingencies increase
Solution Approach 1:
The patent divides the propulsion system into separate controllable modules: the electric motor can be independently decoupled from the propeller and turbine engine systems. The disconnect switch and mechanical decoupling device allow the electric motor to be segmented as an independent unit that can be isolated without affecting the entire propulsion system, thereby managing complexity while maintaining efficiency benefits.
Solution Approach 2:
The patent introduces intermediary components between the electric motor and the rest of the propulsion system: a disconnect switch and mechanical decoupling device. These intermediaries act as mediators that allow the electric motor to be integrated for efficiency while providing a controlled interface for isolation when faults occur, thus managing system complexity.
2Reliability
If redundant systems are added to address contingencies, then safety and reliability are improved, but device complexity increases
Solution Approach 1:
The patent extracts the isolation function from the complex redundant system framework and implements it through dedicated, simple components: a disconnect switch and mechanical decoupling device. This extraction approach provides the necessary safety capability without adding layers of complex redundant control systems, maintaining reliability while limiting complexity growth.
Solution Approach 2:
The disconnect switch and mechanical decoupling device provide self-service isolation capability that operates independently without requiring complex system-wide redundant controls. The electric motor can be isolated through direct pilot action on the disconnect switch, providing safety through self-contained rather than system-dependent mechanisms.
3Reliability
If electric motor isolation capability is added, then fault mitigation and safety are improved, but device complexity increases
Solution Approach 1:
The patent introduces intermediary components between the electric motor and the rest of the propulsion system: a disconnect switch and mechanical decoupling device. These intermediaries act as mediators that allow the electric motor to be integrated for efficiency while providing a controlled interface for isolation when faults occur, thus managing system complexity.
Solution Approach 2:
The patent extracts the isolation function from the complex redundant system framework and implements it through dedicated, simple components: a disconnect switch and mechanical decoupling device. This extraction approach provides the necessary safety capability without adding layers of complex redundant control systems, maintaining reliability while limiting complexity growth.
Data Source
AI summary
A hybrid electric aircraft propulsion system includes both a turbine engine and an electric motor. A power management system controls operation of the electric motor and a pitch angle of a propeller associated with the propulsion system. A disconnect switch is provided to isolate the electric motor by mechanical decoupling the electric motor from the aircraft propulsion system.