Adaptive Speed Setpoint Generation for Aircraft RTA Compliance
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current methods for determining an aircraft's speed profile to observe a Requested Time of Arrival (RTA) are inefficient due to high iteration requirements, convergence difficulties, and inadequate responsiveness to drifts caused by factors like wind gusts or unexpected performance levels, leading to unpredictable and variable calculation workloads and precision issues.
Innovation Solution
A method for continuously and adaptively generating a speed setpoint that is permanently slaved to the time of passage at the RTA point, using weighted proportionality ratios between minimum and maximum speed profiles, and incorporating a tolerance to optimize speed profiles based on flight phases and distance to the RTA constraint, thereby reducing calculation workload and improving responsiveness.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If iterative methods are used to determine speed profile with cost index, then RTA observance can be achieved, but the number of iterations is high and unpredictable
Solution Approach 1:
The patent pre-calculates and stores speed profiles corresponding to different cost indices before flight. During actual flight, the FMS selects from these pre-computed profiles rather than performing iterative calculations, significantly reducing computation time while maintaining RTA observance capability
Solution Approach 2:
The patent divides the speed profile determination into discrete segments based on cost index values. Instead of continuous iterative optimization, the system segments the solution space into predefined cost index levels (e.g., CI=0, CI=50, CI=100) with corresponding pre-computed speed profiles, enabling faster selection during flight
2Measurement precision
If iterative correction of cost index is performed, then convergence can be achieved, but convergence is difficult due to complex behavior of the function
Solution Approach 1:
The system pre-computes speed profiles for multiple cost indices and stores them in a lookup table. During flight, the FMS directly retrieves the appropriate profile based on current cost index without performing iterative corrections, eliminating convergence issues while maintaining ETA accuracy
Solution Approach 2:
The patent creates copies of speed profiles for different cost indices and stores them in the FMS memory. Instead of iteratively correcting a single profile, the system has multiple pre-computed profile copies ready for immediate selection, simplifying the determination process while preserving precision
3Measurement precision
If full recalculation of speed profile is performed for drift compensation, then accuracy is maintained, but calculation must be repeated in full increasing workload
Solution Approach 1:
The patent implements dynamic selection of speed profiles based on real-time drift detection. When drift exceeds thresholds, the FMS switches between pre-computed profiles corresponding to different cost indices, adjusting the selected profile dynamically without requiring full recalculation
Solution Approach 2:
The system changes the cost index parameter to compensate for drift. Instead of recalculating the entire speed profile, the FMS adjusts the cost index value and selects the corresponding pre-computed profile, maintaining accuracy while reducing computational burden
4Measurement precision
If short periodicity calculation is performed, then precise predictions are maintained, but calculation workload increases
Solution Approach 1:
Speed profiles are pre-calculated and stored before flight at various cost indices. During flight, the FMS performs simple lookup and selection operations rather than full calculations, enabling frequent updates with minimal computational load and maintaining precise predictions
Data Source
AI summary
Method for generating a flight speed profile of an aircraft (100) according to an RTA constraint, characterized in that it permanently calculates, at any point of the flight plan, a speed setpoint VΩ(X) of the aircraft determined on the basis of reference speed profiles, comprising at least a minimum speed profile Vmin(X), and a maximum speed profile Vmax(X). The method can also take into account an optimum speed profile Vopt(X) determined, for example, on the basis of a cost or performance index.