Flight Management System Transition Point Determination
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Solution Overview
Problem
Current flight management systems struggle to accurately determine the start and end points of transitions between different aerodynamic configurations and engine speeds during flight, particularly in continuous descent approaches, and fail to account for the dynamic effects of these transitions on flight time.
Innovation Solution
A method that extracts performance data from a database to determine the start and end points of transitions by numerical integration of aircraft dynamics equations, considering variations in aerodynamic configurations, and calculates the temporal impact of transitions on flight time, using either detailed dynamic modeling or heuristic estimation based on available data.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If conventional flight management methods are used to calculate transition points, then the calculation process is simple, but the accuracy of determining start and end points of transitions is insufficient
Solution Approach 1:
The patent applies dynamics by considering the transient behavior of aerodynamic configurations during transition. Instead of treating configurations as static states, the method models the dynamic evolution of drag coefficient and other performance parameters throughout the transition process, enabling accurate determination of start and end points by detecting when actual parameters deviate from or return to expected values.
Solution Approach 2:
The patent implements preliminary action by pre-calculating expected performance data (drag coefficient, speed, altitude) for the entire transition process and storing it in a database. This pre-computed reference data is then used during flight to quickly compare with actual measurements and determine transition points without complex real-time calculations.
2Loss of time
If conventional methods are used to manage aerodynamic configurations, then the system is easier to operate, but the impact of transitions on flight time cannot be accurately determined
Solution Approach 1:
The patent implements feedback by continuously monitoring actual flight parameters (speed, altitude, drag coefficient) during transitions and comparing them with pre-calculated expected values. When deviations exceed thresholds, the system automatically identifies transition start and end points, and calculates their impact on flight time, providing feedback to the flight management system for trajectory optimization.
Solution Approach 2:
The patent replaces complex mechanical timing and manual calculation methods with an automated electronic system that uses pre-stored performance data and real-time sensor measurements. The flight management system automatically determines transition points and calculates their temporal impact without requiring manual intervention or complex real-time physics calculations.
3Measurement precision
If detailed dynamic modeling is used to determine transition points, then the precision of transition determination is improved, but the computational resources required increase
Solution Approach 1:
The patent applies preliminary action by performing all complex dynamic modeling and numerical integration operations before flight, storing the results in a database. During actual flight, the system only needs to retrieve pre-computed expected values and compare them with simple sensor measurements, minimizing real-time computational energy consumption while maintaining high precision.
Data Source
AI summary
A method is provided for managing the flight of an aircraft flying a trajectory calculated by a flight management system. The trajectory necessitates at least one transition between two different aerodynamic configurations of the aircraft. The method comprises: extraction of performance data of the aircraft from a database, at least one item of performance data being a function of an aerodynamic configuration, selection between a first determination step and a second determination step, a step of determination of a start point and of an end point of the transition between two aerodynamic configurations and engine speeds of an aircraft during a flight, the determination step being implemented by the flight management system and chosen from among the first and second determination steps, the determination step calculating the trajectory by numerical integration of the equations representative of the dynamics of the aircraft making use of the performance data of the aircraft.