Hybrid-Electric Propulsion Control Assembly for Signal Validation
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Solution Overview
Problem
Existing control assemblies for hybrid-electric propulsion systems in aircraft are in need of improvement to enhance the identification and validation of control signals for both engine and electric motor operations, particularly in terms of rotation speed and torque, to ensure reliable and efficient propulsion system performance.
Innovation Solution
A control assembly for aircraft propulsion systems that includes a propulsion train sensor assembly, channel A and channel B control units, and a battery management system, which utilize sensors and processors to identify valid and invalid control signals based on engine and electric motor rotation speed and torque measurements, ensuring accurate operation and monitoring of both engine and electric motor components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If control assemblies for hybrid-electric propulsion systems are designed to monitor and validate control signals for both engine and electric motor operations, then system reliability is improved, but device complexity increases due to the need for multiple sensors, processors, and validation channels
Solution Approach 1:
The control assembly is divided into separate channel A and channel B control units, each with dedicated processors for validating control signals. The sensor subassemblies are segmented into engine-specific and electric motor-specific sensors, allowing independent validation of control signals for each propulsion component without requiring a monolithic complex system
Solution Approach 2:
Channel B control units serve as intermediary validation layers that receive control signals from channel A control units and verify their validity before execution. This intermediary validation mechanism ensures reliability by catching invalid control signals without requiring complete system redesign
2Measurement precision
If sensors and processors are added to identify valid and invalid control signals based on rotation speed and torque measurements, then measurement precision is improved, but device complexity increases
Solution Approach 1:
Different sensor subassemblies are designed with specialized measurement capabilities tailored to their specific propulsion components - engine sensors optimized for rotation speed and torque measurement, and electric motor sensors optimized for their respective parameters. This local specialization improves measurement precision without requiring all sensors to be universally complex
Solution Approach 2:
The channel B control units and processors are designed to universally validate control signals across different propulsion components (engine and electric motor) using the same validation logic and measurement principles, reducing overall system complexity through standardized multi-functional validation mechanisms
Data Source
AI summary
An aircraft propulsion system assembly includes an aircraft propulsion system and a control assembly. The aircraft propulsion system includes a propulsor, an engine, and an electrical assembly. The engine is coupled to the propulsor. The electrical assembly includes an electric motor and a battery management system. The electric motor is coupled to the propulsor. The control assembly includes a plurality of channel A control units and at least one channel B control unit. The plurality of channel A control units includes an engine control unit for the engine and an electric motor control unit for the electric motor. The at least one channel B control unit is configured to identify valid and invalid output control signals of the engine control unit. The battery management system is configured to identify valid and invalid output control signals of the electric motor control unit.