Modular Hybrid Electric Propulsion Modeling for Real-Time Control
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Solution Overview
Problem
Existing hybrid electric propulsion systems for aircraft lack an accurate engine model that simulates the coordinated operation of thermal engines and electric motors, hindering development and validation of control systems.
Innovation Solution
A modular engine model is developed for hybrid electric propulsion systems, comprising modules for compressor, turbine, gearbox, air inlet, exhaust, inverter, and electric motor, using executable instructions and mathematical expressions to simulate operational parameters, enabling hardware-in-the-loop and software-in-the-loop analyses.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If a comprehensive engine model simulating coordinated operation of thermal engine and electric motor is developed, then the accuracy of control system development and validation is improved, but the device complexity increases
Solution Approach 1:
The engine model is divided into multiple independent modules including a thermal engine module, an electric motor module, a gearbox module, and control system modules. Each module can be independently developed, validated, and modified, allowing comprehensive simulation while maintaining manageable complexity through modular architecture
Solution Approach 2:
A control system module acts as an intermediary between the thermal engine module and electric motor module, coordinating their operation and managing power distribution. This mediator enables accurate simulation of coordinated operation while encapsulating complexity within the control logic layer
2Productivity
If real-time execution capability is improved for control system validation, then the productivity of development and testing is enhanced, but the manufacturing precision requirements increase
Solution Approach 1:
The engine model is designed with dynamic characteristics that allow real-time execution while maintaining accuracy. The modular architecture enables selective level of detail in different modules, optimizing the balance between computational speed and simulation fidelity for real-time control system validation
Solution Approach 2:
The model allows dynamic adjustment of operational parameters and can operate at different fidelity levels depending on the validation needs. This enables real-time execution for routine testing while allowing higher precision modes for critical validation scenarios
Data Source
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AI summary
A method of modeling the operation of a HEP system (20) for an aircraft is provided. The HEP system includes a gas turbine engine (32) and an electric motor (24). The method includes: modeling the operation of a HEP system using an engine model (54) with a plurality of modules (58). Each module (58) is configured with executable instructions to receive an input operational parameter and produce an output operational parameter. The input operational parameters include one or more of an input pressure, temperature, mass flow, or power, and the output operational parameters include one or more of an output pressure, temperature, mass flow, or power. The modeling includes providing a first output operational parameter from a first module (58) to a second module (58) as a first input operational parameter, and using the second module (58) to produce a second output operational parameter using the first input operational parameter.