Model-Based Controller for Turboprop Engine and Propeller Coordination
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Solution Overview
Problem
Traditional turboprop engine control systems require separate levers for engine and propeller control, which can be cumbersome and inefficient, especially in situations where simultaneous modulation of engine power and propeller thrust is needed.
Innovation Solution
A model-based controller system that simultaneously adjusts engine and propeller parameters by formulating optimization problems based on engine and propeller models, target output power, and speed, using fuel flow, beta angle, and other parameters to optimize engine and propeller control commands.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If separate control systems are used for engine and propeller, then each component can be controlled independently, but the control system complexity and operational burden increase
Solution Approach 1:
The patent combines the engine control system and propeller control system into a single integrated control unit. This controller receives pilot inputs and simultaneously determines both engine power output and propeller parameters (rotational speed and blade pitch angle) through optimization algorithms, eliminating the need for separate control systems and reducing operational complexity.
Solution Approach 2:
The integrated control system performs multiple functions: it controls engine fuel flow, adjusts propeller rotational speed, modifies blade pitch angle, and optimizes the coordination between engine and propeller. This multi-functional approach allows a single control system to replace what would traditionally require separate dedicated systems for each function.
2Productivity
If simultaneous modulation of engine power and propeller thrust is needed, then operational efficiency improves, but separate control systems become cumbersome
Solution Approach 1:
The patent merges engine control and propeller control into one integrated system that simultaneously modulates both engine power output and propeller thrust parameters. The controller uses optimization algorithms to coordinate fuel flow, rotational speed, and blade pitch angle adjustments in real-time, enabling efficient simultaneous modulation without requiring separate control systems.
Solution Approach 2:
The control system dynamically adjusts multiple parameters (engine power, propeller speed, blade pitch) simultaneously based on real-time optimization. The system continuously solves optimization problems to determine the optimal combination of engine and propeller settings, allowing dynamic and coordinated modulation of both components for improved operational efficiency.
3Manufacturing precision
If a model-based optimization approach is used, then control precision and coordination improve, but computational complexity increases
Solution Approach 1:
The patent pre-establishes mathematical models of the engine and propeller systems, including their performance characteristics and operating limits. These models are prepared in advance and stored in the control system, allowing the controller to quickly solve optimization problems by referencing pre-defined relationships rather than calculating fundamental physics in real-time, thus reducing computational complexity while maintaining precision.
Solution Approach 2:
The patent uses simplified mathematical models that replicate the essential behavior of the complex engine and propeller systems. These models capture the key relationships between control inputs and outputs without requiring full physical fidelity, enabling the optimization algorithm to achieve sufficient control precision with reduced computational complexity compared to using complete physical models.
Data Source
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AI summary
Systems (200) and methods (500) for controlling a gas turbine engine (100) and a propeller (120) are described herein. A target output power for the engine (100) and a target speed for the propeller (120) are received. A measurements of at least one engine parameter and a measurement of at least one propeller parameter are received. At least one engine control command is generated based on the target output power, the measurement of the at least one engine parameter and at least one model of the engine (100). At least one propeller control command is generated based on the target speed, the measurement of the at least one propeller parameter and the at least one model of the propeller (120). The at least one engine control command is output for controlling an operation of the engine (100) accordingly and the at least one propeller control command is output for controlling an operation of the propeller (120) accordingly.