Aircraft Propulsion Control Assembly Using Speed-Torque Signal Checks
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Solution Overview
Problem
Existing control assemblies for hybrid-electric propulsion systems in aircraft are in need of improvement to enhance reliability and efficiency in controlling both engine and electric motor operations, particularly in identifying valid and invalid control signals.
Innovation Solution
A control assembly with a propulsion system sensor assembly and channel A and B control units, including a processor to identify valid and invalid output control signals based on rotation speed and torque measurements, reducing the need for discrete, independent control units.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If multiple discrete, independent control units are used for engine and electric motor operations, then control functionality is comprehensive, but system weight, cost, and complexity increase
Solution Approach 1:
The patent combines multiple discrete control units into a single integrated control unit that manages both the engine and electric motor operations. This consolidation reduces the number of separate components while maintaining comprehensive control functionality through a unified processing architecture that handles various control signals and coordinates operations of different propulsion elements.
Solution Approach 2:
The integrated control unit is designed with multi-functional capabilities to perform diverse control tasks including engine management, electric motor control, signal validation, and coordination of hybrid-electric propulsion operations. This universal controller replaces multiple specialized control units, reducing system complexity while preserving all necessary control functions.
2Adaptability or versatility
If multiple discrete, independent control units are used for engine and electric motor operations, then control functionality is comprehensive, but system weight increases
Solution Approach 1:
The patent consolidates multiple discrete control units into a single integrated control unit, thereby reducing the total weight of the control system. This merging eliminates redundant structural elements, housing, and mounting requirements associated with multiple separate units while maintaining all necessary control capabilities through integrated processing and coordination functions.
3Adaptability or versatility
If multiple discrete, independent control units are used for engine and electric motor operations, then control functionality is comprehensive, but system cost increases
Solution Approach 1:
The integrated control unit consolidates multiple discrete control units into a single component, reducing manufacturing costs through economies of scale, simplified assembly processes, and reduced inventory requirements. The unified design allows for standardized production and integration, lowering overall system cost while maintaining comprehensive control functionality.
4Ease of operation
If discrete control units are used for engine and electric motor, then control signals can be independently processed, but reliability in identifying valid and invalid signals decreases
Solution Approach 1:
The integrated control unit incorporates feedback mechanisms that continuously monitor control signals from both the engine and electric motor systems. By centralizing signal processing and validation, the system can cross-check signals against established parameters and operational states, improving the reliability of identifying valid and invalid control signals through coordinated feedback loops.
Solution Approach 2:
The integrated control unit acts as an intermediary that receives, validates, and coordinates control signals from multiple sources. This central mediation allows for comprehensive signal verification against system state and operational parameters, improving reliability by preventing invalid signals from affecting system operation while maintaining the ability to independently process different signal types.
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 electric motor. The engine includes a rotational assembly coupled to the propulsor. The electric motor includes a rotor coupled to the propulsor. The control assembly includes a propulsion system sensor assembly, a plurality of channel A control units, and at least one channel B control unit. The propulsion system sensor assembly is configured to measure one or both of a rotation speed and a torque of the propulsor. The plurality of channel A control units includes an engine control unit and an electric motor control unit. The channel B control unit is configured to identify valid and invalid output control signals of the engine control unit and the electric motor control unit using the one or both of the rotation speed and the torque.