Aircraft Engine Thrust Matching for Transient Asymmetry Control
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Solution Overview
Problem
Existing methods struggle to effectively match the transient and steady-state characteristics of original engines with new powerplants in aerospace applications, particularly during fast transients and when thrust asymmetry is significant, which can compromise safety and handling characteristics.
Innovation Solution
A method and system that utilize a controller to apply modified commanded thrust to new powerplants, emulating the characteristics of incumbent powerplants through the use of open control loops and models, such as non-linear equations or N-dimensional tables, to ensure consistent aircraft performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If automated control systems are used to compensate for multiple engine thrust asymmetry, then handling characteristics during fast transients are improved, but system cost increases significantly
Solution Approach 1:
The patent creates a mathematical model that copies the thrust characteristics of the incumbent engine. By using a lookup table storing thrust values from the incumbent engine and interpolating between these values, the system replicates the original engine's behavior without requiring expensive automated control hardware. The model includes parameters such as compressor inlet temperature, shaft speed, and thrust to accurately reproduce the incumbent engine's performance characteristics.
Solution Approach 2:
The patent replaces the mechanical automated control system with a computational model. Instead of using physical sensors, actuators, and control algorithms to compensate for thrust asymmetry, the system uses a mathematical representation of the incumbent engine that calculates equivalent thrust commands for the new engine, substituting complex mechanical control infrastructure with software-based modeling.
2Stability of the object's composition
If pilot adjusts aircraft control surfaces to manage multiple engine thrust asymmetry, then steady state performance is maintained, but performance during fast transients deteriorates
Solution Approach 1:
The patent performs preliminary action by pre-calculating and storing thrust characteristics of the incumbent engine in a lookup table before flight. During flight, the system quickly retrieves and interpolates pre-computed thrust values rather than calculating them in real-time, enabling rapid response during fast transients while maintaining steady state accuracy. This pre-computation approach allows the system to provide immediate thrust compensation without delay.
3Productivity
If new powerplant is installed to update aircraft, then productivity and efficiency are improved, but matching transient characteristics with original engine becomes difficult
Solution Approach 1:
The patent uses parameter changes to bridge the gap between new and incumbent engines. The model transforms thrust commands by adjusting parameters such as compressor inlet temperature, shaft speed, and mass flow rate based on the relationship between the new engine's performance maps and the incumbent engine's characteristics. This parameter transformation allows the more efficient new engine to replicate the transient response of the original engine.
Data Source
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AI summary
A method of controlling a multi-engine aircraft (102) includes receiving input for commanded thrust and modifying the commanded thrust using a model of an incumbent powerplant (108) to generate a modified commanded thrust for matching aircraft performance with a new powerplant (104) to the aircraft performance with the incumbent powerplant (108). The method includes applying the modified commanded thrust to the new powerplant (104).