Hybrid Propulsion Power Control for Stable Aircraft Energy Transfer
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Solution Overview
Problem
Existing hybrid propulsion systems face challenges in maintaining stability and availability of power due to conflicting control requirements between propulsion and overall energy systems, leading to instability and operability issues during transitions between power injection and draw modes.
Innovation Solution
A method and system that dynamically switch control authority between an overall aircraft power control unit and a hybrid propulsion system control unit based on operability limits, ensuring seamless transitions and optimized power management by monitoring and controlling power generation and distribution across propulsive and non-propulsive energy sources.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If the electrical network controls the power drawn off the turbomachine, then the power supply to loads is optimized, but the stability of the electrical network and availability of power for turbomachine operability deteriorate
Solution Approach 1:
The patent implements dynamic control mode switching between two operational states: a first mode where the electrical network controller regulates power drawn from the turbomachine, and a second mode where the propulsion system controller regulates power injected into or drawn from the turbomachine. The system automatically transitions between these modes based on real-time monitoring of turbomachine operability parameters, ensuring optimal performance while maintaining stability and reliability.
Solution Approach 2:
The system continuously monitors the operability of the turbomachine and uses this feedback to determine when to switch between control modes. The feedback mechanism tracks parameters such as surge margin, temperature limits, and power availability, enabling the control system to respond adaptively to changing operational conditions and maintain system stability.
2Reliability
If the turbomachine controls the power drawn off the electrical network, then the operability of the turbomachine is maintained, but the stability of the electrical network and power flow continuity deteriorate
Solution Approach 1:
The system dynamically adjusts control authority based on turbomachine operating conditions. When the turbomachine approaches operability limits, the control mode switches to prioritize turbomachine protection. When operating within safe margins, the system transitions to a mode that prioritizes electrical network stability, thereby adaptively balancing both requirements.
Solution Approach 2:
The control system acts as an intermediary that coordinates between the electrical network controller and the propulsion system controller. It manages the transition of control authority smoothly, ensuring that neither system destabilizes the other during mode switches, and maintaining overall system coherence through centralized coordination.
3Adaptability or versatility
If control authority switches between propulsion system and electrical network, then adaptability to different operating conditions is improved, but the stability of the electrical network and power flow continuity worsen
Solution Approach 1:
The system performs preliminary assessments of turbomachine operability parameters before initiating control mode transitions. By evaluating surge margin, temperature conditions, and power availability in advance, the system determines the optimal switching point, preventing abrupt transitions that could disrupt power flow continuity or destabilize the electrical network.
Solution Approach 2:
Continuous feedback monitoring of turbomachine operability enables the system to detect when transition conditions are met. The feedback loop ensures that control authority switches only when necessary and appropriate, maintaining power flow continuity by avoiding unnecessary mode changes and ensuring smooth transitions when they occur.
Data Source
AI summary
A method of control of a power generation and control system of an aircraft including: a hybrid propulsion system including an electrical network and a propulsive energy source, at least one non-propulsive energy source, a control unit of the hybrid propulsion system, and an overall aircraft power control unit, characterized in that the method includes: the determination of an operability limit of the propulsive energy source, the monitoring of the operability of the propulsive energy source by the control unit of the hybrid propulsion system, and the control of a power generated by the propulsive energy source by the overall aircraft power control unit when the operability of the propulsive energy source is less than said determined operability limit or the control of a power generated by the propulsive energy source by the control unit of the hybrid propulsion system.