Hybrid Aircraft ECU Torque Split for Takeoff and Cruise
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Solution Overview
Problem
Aircraft engines are often oversized for takeoff thrust requirements, leading to inefficiencies during cruising, as they produce more power than needed, and there is a need for improved hybrid electric propulsion systems to optimize power distribution between heat engines and electric motors.
Innovation Solution
A hybrid electric engine control module (ECU) that dynamically splits torque between a heat engine and an electric motor system based on real-time parameters, including battery state of charge, sensor information, and operational constraints, to optimize power output and conserve energy.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If aircraft engines are sized to produce maximum thrust for takeoff, then takeoff performance is improved, but fuel consumption increases during cruising
Solution Approach 1:
The propulsion system is segmented into two independent power sources: a heat engine and an electric motor system. This allows the total power requirement to be divided between combustion-based thrust and electrically-driven thrust, enabling flexible power distribution during different flight phases to optimize fuel consumption while maintaining takeoff performance.
Solution Approach 2:
The hybrid electric engine control module dynamically adjusts the torque split between the heat engine and electric motor in real-time based on flight conditions. During takeoff, the system can maximize combined power output, while during cruising, it optimizes the ratio to minimize fuel consumption, thus resolving the contradiction between peak power availability and steady-state efficiency.
2Use of energy by moving object
If the heat engine provides all power during cruising, then fuel consumption is maximized, but if electric motor provides power, then battery discharge increases
Solution Approach 1:
The control module continuously monitors and adjusts operational parameters including battery state of charge, heat engine torque output, and electric motor torque contribution. By dynamically changing these parameters based on real-time conditions, the system optimizes the balance between fuel consumption and battery discharge, ensuring efficient operation across varying flight phases.
Solution Approach 2:
The hybrid electric engine control module implements closed-loop feedback control by monitoring battery state of charge, sensor information, and operational constraints. This feedback mechanism allows the system to adjust the torque split between heat engine and electric motor to maintain optimal energy management, preventing excessive battery discharge while minimizing fuel consumption during cruising.
3Duration of action of moving object
If the ECU optimizes power distribution to reduce fuel consumption, then flight duration is extended, but power availability during peak demand may be limited
Solution Approach 1:
The battery system is pre-charged and the heat engine is sized to provide base power requirements. During low-power phases such as cruising, the heat engine operates efficiently while the battery maintains charge or charges. This preliminary energy storage ensures that when peak power is needed during takeoff or climb, both power sources can contribute maximum power, thus extending flight duration without compromising peak power availability.
Data Source
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Figure 3A
AI summary
A hybrid electric engine control module (ECU) configured to be operatively connected to a hybrid electric aircraft powerplant having a heat engine system and an electric motor system to control a torque output from each of the heat engine system and the electric motor system, the ECU being configured to determine whether the electric motor system and/or the heat engine system are in a normal mode such that the electric motor system and/or the heat engine can provide a predetermined amount of torque (e.g., full power). The ECU can be configured to receive a total torque setting and split output power between the electric motor system and the heat engine system in accordance with the normal mode as a function of the total torque setting. The ECU can be configured to detect and command recharging or regenerating of the battery system in some flight conditions.