Hybrid Electric Propulsion Modeling for Real-Time Controller Evaluation
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Solution Overview
Problem
Existing engine models for hybrid electric propulsion systems in aircraft fail to accurately simulate the coordinated operation of thermal engines and electric motors, limiting their effectiveness in development and validation of aircraft control systems.
Innovation Solution
A modular engine model is developed, comprising modules for the compressor, turbine, gearbox, air inlet, exhaust, inverter, and electric motor, using executable instructions and mathematical expressions to simulate the operation of a hybrid electric propulsion system, allowing for both steady-state and transient modes, and incorporating hardware-in-the-loop and software-in-the-loop analyses.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If a traditional integrated engine model is used, then the model structure is simple, but the accuracy of simulating coordinated operation of thermal engine and electric motor is insufficient
Solution Approach 1:
The engine model is divided into multiple independent modules (compressor module, turbine module, gearbox module, electric motor module, inverter module, etc.), each representing a specific component. Each module can be independently configured and executed, allowing for accurate simulation of the coordinated operation while maintaining manageable complexity through modular architecture.
2Measurement precision
If a detailed modular model with multiple modules is used, then the simulation accuracy is improved, but the computational complexity and execution time increase
Solution Approach 1:
The model incorporates dynamic operational parameters that can be adjusted in real-time during simulation. The executable instructions enable dynamic calculation of operational parameters based on current system state, allowing the model to adapt to varying operating conditions while maintaining computational efficiency through optimized dynamic responses.
Solution Approach 2:
The model uses configurable operational parameters (input pressure, input temperature, input mass flow, input power, output pressure, output temperature, output mass flow, output power) that can be dynamically changed during execution. This allows the same modular structure to accurately simulate different operating scenarios without increasing fundamental computational complexity.
3Adaptability or versatility
If the model includes comprehensive modules for all system components, then the completeness of the simulation is improved, but the difficulty of configuring and executing the model increases
Solution Approach 1:
The comprehensive model is segmented into discrete, independently configurable modules. Each module (compressor, turbine, gearbox, electric motor, inverter) can be individually configured with its own operational parameters and executable instructions, making the overall complex system easier to configure through modular assembly rather than monolithic configuration.
Data Source
AI summary
A method of modeling the operation of a HEP system for an aircraft is provided. The HEP system includes a gas turbine engine and an electric motor. The method includes: modeling the operation of a HEP system using an engine model with a plurality of modules. Each module 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 to a second module as a first input operational parameter, and using the second module to produce a second output operational parameter using the first input operational parameter.