Dynamic Low Airspeed Warning Threshold for Aircraft
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Solution Overview
Problem
Traditional aircraft warning systems employ a constant scale factor for generating low airspeed warnings, which is insensitive to altitude and engine thrust data, resulting in increased response time and cognitive workload in low altitude situations, necessitating a system that adjusts the low airspeed threshold based on these variables.
Innovation Solution
A method and system that receive engine thrust and aircraft altitude data to determine a variable scale factor, which is used to calculate a dynamic low airspeed threshold, triggering alerts earlier in low altitude conditions by modifying the stick shaker speed and minimum operating speed.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of time
If a constant predetermined scale factor is used for low airspeed warning, then the system is simple to operate, but the response time is insufficient in low altitude situations
Solution Approach 1:
The patent applies dynamics by transitioning from a static, constant scale factor to a dynamic scale factor that varies based on real-time aircraft conditions. The scale factor is now a function of altitude and engine thrust parameters, allowing the low airspeed warning system to adapt its response characteristics to different flight phases and conditions, thereby reducing response time in critical low altitude situations without requiring overly complex system architecture
Solution Approach 2:
The patent implements parameter changes by modifying the scale factor parameter based on altitude and engine thrust data. Instead of using a fixed predetermined value, the system calculates a variable scale factor that changes according to current flight parameters, enabling optimized response time across different operating conditions while maintaining manageable system complexity through parameter-based adaptation
2Ease of operation
If a constant scale factor is used, then the system is easy to manufacture and implement, but it increases cognitive workload for pilots in low altitude situations
Solution Approach 1:
The patent applies feedback by continuously monitoring altitude and engine thrust parameters and using this information to dynamically adjust the scale factor. This closed-loop approach allows the system to automatically adapt to changing flight conditions, providing timely warnings that reduce pilot cognitive workload and response time without requiring manual intervention or complex pilot decision-making
Solution Approach 2:
The system performs self-service by automatically calculating and adjusting the scale factor based on sensed aircraft parameters. The low airspeed warning system self-regulates its behavior according to flight conditions without requiring pilot input or manual configuration, thereby reducing cognitive workload while maintaining optimized response characteristics
Data Source
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AI summary
A method and system are provided for generating a low airspeed warning in an aircraft. This method creates a scale factor that is a factor of engine thrust and aircraft altitude. A low airspeed threshold is determined that varies according to the aircraft altitude with respect to a predetermined altitude band and the engine thrust with respect to a predetermined engine thrust band. A low airspeed alert is generated in response to the determination of the low airspeed threshold. This method provides a pilot with earlier knowledge of low airspeed conditions when the aircraft is in a target altitude band, increasing the pilot's response time and thereby enhancing overall aircraft safety.