Autothrottle Retard Initiation Height Control
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Solution Overview
Problem
Existing systems for determining the height to initiate autothrottle retard during aircraft landing rely on fixed heights, which can lead to unsafe landing scenarios due to either rapid descent or stalling, increasing the risk of structural damage and fatalities.
Innovation Solution
A method and system that dynamically determine the autothrottle retard initiation height based on the aircraft's ground speed, vertical speed, and vertical landing speed factor, allowing for a more suitable height determination for specific landing situations by considering factors like aircraft weight and ground speed.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a fixed height is used for autothrottle retard initiation, then the system is simple to operate, but the landing safety is compromised due to inability to adapt to varying landing conditions
Solution Approach 1:
The patent transforms the fixed, static retard initiation height into a dynamic value that adapts to real-time flight conditions. The system continuously monitors ground speed, vertical speed, and flight path angle, and adjusts the retard initiation height accordingly using the formula H = f(GS, VS, FPA). This dynamic adjustment allows the autothrottle system to optimize landing performance for each specific approach condition while maintaining automated operation.
Solution Approach 2:
The invention changes the parameter of retard initiation height from a fixed constant to a variable determined by multiple flight parameters. By incorporating ground speed, vertical speed, and flight path angle as input parameters, the system calculates an optimized initiation height that accounts for varying aircraft weight, approach speed, and environmental conditions, thereby improving landing safety without requiring manual pilot intervention.
2Strength
If retard initiation height is set too low, then the aircraft structure is protected from excessive descent, but the aircraft may stall due to insufficient deceleration distance
Solution Approach 1:
The system employs feedback mechanisms by continuously monitoring ground speed, vertical speed, and flight path angle during the approach phase. These real-time measurements are fed into the calculation formula to determine the optimal retard initiation height. The feedback loop ensures that the system can predict the required deceleration distance based on current flight conditions and adjust the initiation height accordingly, preventing both excessive descent and stall conditions.
Solution Approach 2:
The patent calculates and determines the optimal retard initiation height in advance, before the aircraft reaches the critical landing phase. By using the formula H = f(GS, VS, FPA) during the approach segment, the system preliminarily establishes the precise height at which autothrottle retard should begin, ensuring sufficient distance for speed reduction while maintaining structural safety margins.
3Reliability
If retard initiation height is set too high, then the aircraft has sufficient distance to decelerate, but the aircraft may experience excessive descent rate and structural stress
Solution Approach 1:
The system dynamically adjusts the retard initiation height by incorporating vertical speed and flight path angle as key parameters in the calculation formula. This parameter-based approach ensures that the initiation height is optimized for each specific approach condition, providing sufficient deceleration distance when needed while avoiding excessive descent rates that would impose harmful structural stress on the aircraft.
Data Source
AI summary
An autothrottle retard initiation method includes receiving an aircraft's ground speed, receiving the aircraft's vertical speed, determining autothrottle retard initiation height based on the aircraft's ground speed, the aircraft's vertical speed, and an aircraft vertical landing speed factor, receiving the aircraft's height above ground, and initiating autothrottle retard when the aircraft's height above ground and the autothrottle retard initiation height are equal.