Aircraft Climb Thrust Control Using Dynamic DTflex Adjustment
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Solution Overview
Problem
Existing methods for optimizing the climb phase of an aircraft are sub-optimal in terms of fuel consumption and cost, as they often result in ineffective thrust usage during the climb phase.
Innovation Solution
A method and device that continuously adapt the optimized DTflex value based on current aircraft conditions, using an avionic computer to acquire and process input parameters and retrieve optimized DTflex values from a database, to modulate thrust and minimize fuel consumption.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If maximum available thrust is used during take-off and climb-out, then the aircraft achieves sufficient thrust for take-off and climb, but the engines are subjected to high stresses and high exhaust gas temperatures which reduces engine lifespan and increases maintenance costs
Solution Approach 1:
The patent applies dynamics by continuously adapting the DTflex value during the climb phase based on real-time aircraft conditions (weight, speed, altitude). Instead of using a static thrust limit, the system dynamically adjusts the thrust differential to optimize the balance between required thrust and engine stress, allowing the aircraft to operate at optimal thrust levels at each phase of the climb.
Solution Approach 2:
The patent changes the parameter DTflex (temperature differential) to control thrust. By computing an optimized DTflex value that varies with aircraft conditions, the system modifies the thrust parameter to reduce engine stresses and exhaust gas temperatures while maintaining sufficient climb performance, thereby extending engine lifespan and reducing maintenance costs.
2Adaptability or versatility
If a predefined thrust limit is used during take-off, then the aircraft takes off with a certain percentage of maximum thrust, but this method is not suitable for a wide range of take-off weights and results in sub-optimal fuel consumption
Solution Approach 1:
The system dynamically adjusts the DTflex value during the climb phase based on real-time aircraft conditions including weight, speed, and altitude. This dynamic adaptation allows the thrust limitation strategy to be optimized for different take-off weights and climb phases, eliminating the need for a single predefined thrust limit and thereby optimizing fuel consumption across various operating conditions.
Solution Approach 2:
The patent implements feedback by continuously monitoring aircraft conditions (weight, speed, altitude) and using this information to determine the optimized DTflex value at each moment during the climb. This closed-loop approach ensures that the thrust limitation is continuously optimized for current conditions, improving both adaptability to different weights and fuel efficiency compared to static predefined limits.
3Ease of operation
If a constant flex temperature is used in the autoderate or flex-temp method, then the aircraft can take off with reduced thrust based on weight, but the constant flex temperature is not the most suitable at every point during the climb phase and leads to excess fuel consumption
Solution Approach 1:
The patent transforms the static flex-temp method into a dynamic system by continuously computing and adjusting the DTflex value during the climb phase based on current aircraft conditions. This dynamic adjustment ensures that the thrust limitation remains optimal throughout the entire climb, rather than using a constant flex temperature that becomes sub-optimal as flight conditions change, thereby reducing excess fuel consumption.
Solution Approach 2:
The system uses feedback from real-time measurements of aircraft weight, speed, and altitude to continuously determine the optimized DTflex value. This feedback mechanism allows the system to maintain flexibility in thrust selection while adapting to changing climb conditions, ensuring optimal fuel efficiency throughout the climb phase rather than relying on a predetermined constant flex temperature.
Data Source
AI summary
A method for optimizing a climb phase of an aircraft, implemented repeatedly during the climb phase, includes an acquiring step for acquiring current values of input parameters, a determining step for determining a current optimized DTflex value from the current values of the input parameters and from optimized DTflex values recorded in a database and a transmitting step for transmitting the determined current optimized DTflex value to a user system with a view to controlling the thrust of the aircraft, the method making it possible to continuously adapt, during the climb phase, the optimized DTflex value so it corresponds to current conditions of the aircraft to maximize its performance particular for fuel consumption.