Aircraft Engine Synchronization Control Logic
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Solution Overview
Problem
Existing engine synchronization methods for aircraft twin-spool turbojet engines are either fully automatic, leading to potential risks when conditions are not favorable, or require pilot validation in all cases, which can be distracting and inefficient, affecting engine performance and passenger comfort.
Innovation Solution
A synchronization method with additional activation states (deactivated, armed, and enabled) that requires pilot validation when safety conditions are not met, allowing for automatic reactivation when conditions are safe and optimizing engine performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If synchronization is activated automatically when conditions are met, then reactivation is efficient and avoids pilot distraction, but engine safety risks increase when conditions are unfavorable
Solution Approach 1:
The system dynamically adjusts the activation mode between automatic and manual based on engine safety conditions. When conditions are favorable, automatic reactivation occurs for efficiency; when conditions are unfavorable, manual pilot validation is required, creating a dynamic adaptation to operational context
Solution Approach 2:
The system continuously monitors engine parameters (N2 speed, Ps3 pressure, Q ratio) and uses this feedback to determine whether automatic reactivation is safe. The feedback loop enables the system to distinguish between favorable and unfavorable conditions, adjusting the activation mode accordingly
2Reliability
If pilot validation is required for all synchronization activations, then engine safety is ensured, but pilot distraction and operational inefficiency increase
Solution Approach 1:
The activation process is segmented into two distinct pathways: automatic reactivation for favorable conditions and manual validation for unfavorable conditions. This segmentation allows the system to minimize pilot workload when safe while maintaining safety oversight when needed
3Reliability
If synchronization is deactivated due to safety conditions, then engine protection is ensured, but engine availability and performance degrade
Solution Approach 1:
The system transitions between deactivated and automatically reactivated states based on real-time engine conditions. When safety conditions are favorable, the system dynamically reactivates synchronization without pilot intervention, maximizing engine availability while maintaining protection when conditions deteriorate
Data Source
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AI summary
Method of synchronising the engines of an aircraft. Method of synchronising the engines of an aircraft, according to at least one activation logic (10, 10') defining a deactivated state (20), an armed state (22) and at least one activated state (16, 18), and comprising: -switching (32) of the synchronisation from the deactivated state to the armed state when an activation order is issued by a pilot of the aircraft; -switching (36) of the synchronisation from the armed state to the activated state when at least certain safety and/or activation conditions are satisfied; and -switching (24, 34) of the synchronisation from the activated or armed state to the deactivated state when a deactivation order is issued by the pilot or when at least a part of the safety conditions are not satisfied.