Aircraft Descent Profile Control With Variable Thrust Back-Calculation
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Solution Overview
Problem
Current flight management systems (FMS) rely on outdated assumptions and constant values for aircraft performance characteristics during descent, which are inefficient and do not account for variable parameters, leading to suboptimal fuel consumption and flight time.
Innovation Solution
A method and system that determine a descent profile by receiving aircraft performance characteristics, calculating a first aircraft energy level, and repeatedly back-calculating subsequent models to determine variable thrust parameters based on a minimizing cost profile, allowing for an optimized descent trajectory.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If prior FMS use constant values for aircraft performance characteristics during descent, then the system complexity is reduced and ease of operation is improved, but fuel consumption efficiency deteriorates and flight operation costs increase
Solution Approach 1:
The patent applies dynamics by transitioning from static constant values to dynamic variable parameters. The system repeatedly back-calculates aircraft performance models with successively larger energy levels to determine variable thrust parameters, allowing the descent profile to adapt dynamically to changing aircraft energy states and performance characteristics throughout the descent phase.
Solution Approach 2:
The patent implements parameter changes by modifying the thrust parameter from a constant value to a variable parameter. The controller repeatedly back-calculates models to determine optimal variable thrust parameters based on minimizing cost profiles, thereby changing the operational parameters from fixed to adaptive values that optimize fuel consumption.
2Device complexity
If prior FMS use constant values for aircraft performance characteristics, then the device complexity is reduced, but fuel consumption efficiency and flight operation costs worsen
Solution Approach 1:
The system transitions from static to dynamic operation by repeatedly back-calculating performance models with varying energy levels. This dynamic approach allows the FMS to adapt thrust parameters in real-time based on aircraft energy state, optimizing fuel consumption without requiring complex hardware modifications.
Solution Approach 2:
The FMS performs self-service by automatically repeatedly back-calculating the set of subsequent models and determining optimal variable thrust parameters without external intervention. The system uses its own computational resources to optimize the descent profile, reducing the need for external flight management assistance.
3Use of energy by moving object
If variable thrust parameters are determined through repeated back-calculating, then fuel consumption is minimized and flight operation costs are reduced, but the computing time and processing complexity increase
Solution Approach 1:
The system performs preliminary action by pre-calculating and storing a set of subsequent performance models with successively larger energy levels before the actual descent. During descent, the controller can quickly reference and select from these pre-prepared models rather than performing full calculations in real-time, reducing computing time while maintaining optimization benefits.
Solution Approach 2:
The patent implements dynamics by using a hybrid approach where the computationally intensive back-calculation is performed in advance to create a library of optimized models, and then dynamic selection from these pre-calculated models occurs during actual descent operations. This balances the need for optimization with real-time computing constraints.
Data Source
AI summary
A method and system of determining or estimating a descent profile includes receiving a final approach fix for a target destination, repeatedly back-calculating a set of subsequent models, determining a descent profile based on the repeated back-calculating the set of subsequent models, and operating the aircraft in accordance with the descent profile.