Aircraft Engine Cutoff Authorization Logic
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Solution Overview
Problem
Existing systems for aircraft engine propulsion faults, such as thrust malfunctions, do not allow for safe and controlled engine cutoff or reduction in all flight phases and states, posing a safety risk.
Innovation Solution
A device that determines specific aircraft parameters, including throttle lever position and flight state, to issue an authorization signal allowing controlled engine action, ensuring safety conditions are met before engine cutoff or reduction is initiated.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If automatic engine cutoff is implemented to address propulsion faults, then safety is improved, but the system cannot operate in all flight phases and states
Solution Approach 1:
The patent implements dynamic adaptability by making the engine cutoff system conditional on real-time flight parameters. The control system continuously monitors flight phase, aircraft state, and engine parameters to dynamically enable or disable the automatic cutoff function. This resolves the contradiction by allowing the safety feature to operate adaptively across different flight conditions rather than being statically restricted or universally applicable.
Solution Approach 2:
The system changes its operational parameters based on flight conditions. By monitoring parameters such as flight phase, aircraft attitude, and engine status, the system adjusts its responsiveness and authorization to execute engine cutoff. This parameter-based control enables the system to maintain safety while adapting to the specific constraints of each flight phase.
2Adaptability or versatility
If engine cutoff is authorized in more flight phases, then adaptability is improved, but safety risks increase without proper condition verification
Solution Approach 1:
The patent applies preliminary action by verifying all necessary safety conditions before authorizing engine cutoff. The control system checks multiple parameters including flight phase, aircraft state, and engine status in advance of any cutoff action. This preliminary verification ensures that the system only executes engine cutoff when safe to do so, preventing premature or unsafe interventions while maintaining adaptability across flight phases.
Solution Approach 2:
The system implements continuous feedback monitoring of flight parameters and aircraft state to dynamically determine whether engine cutoff authorization is appropriate. This feedback mechanism allows the system to adapt to changing flight conditions in real-time, enabling cutoff in phases where it is safe while preventing it in phases where it would be hazardous.
3Reliability
If multiple parameters are monitored to ensure safety conditions, then reliability is improved, but device complexity increases
Solution Approach 1:
The patent employs a multi-functional control system that handles multiple parameters and safety checks through a unified architecture. The same control unit that manages normal engine operation also performs safety verification and cutoff authorization, eliminating the need for separate dedicated systems for each function. This universal approach maintains high reliability through comprehensive monitoring while avoiding the complexity of multiple independent systems.
Data Source
AI summary
A device for issuing authorization to act on the operating conditions of an aircraft engine and engine control system includes a first unit for determining particular parameters concerning the aircraft, including the position of a power lever controlling the supply of fuel to the engine, and a second unit for determining, based on the particular parameters, whether the aircraft is in a state authorizing an action on the operating conditions of the engine and for issuing, as the case may be, a corresponding authorization signal.