Aircraft Trajectory Calculation Engine for Isochrone Optimization
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Solution Overview
Problem
Existing aircraft mission calculation systems are inadequate for business aviation, as they require multiple iterations to adjust to variable mission criteria and do not optimize routes based on real-time meteorology and customer constraints, often relying on established air routes that do not account for performance and comfort factors.
Innovation Solution
A mission calculation system that integrates a calculation engine with a user interface and databases for meteorological and navigation data, capable of calculating isochronous curves and iso-fuel consumption curves to determine optimal trajectories considering aircraft performance, passenger comfort, and meteorological conditions, allowing for rapid adjustments to mission parameters.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If conventional flight plan systems use pre-established air routes and single-input criteria, then the system complexity is reduced, but the adaptability to variable mission criteria and real-time conditions deteriorates
Solution Approach 1:
The system dynamically adjusts flight parameters by calculating multiple trajectory options based on varying mission criteria, weather conditions, and aircraft performance. The calculation engine continuously optimizes trajectories rather than relying on fixed pre-established routes, allowing the system to adapt to changing conditions while maintaining manageable complexity through automated computations.
Solution Approach 2:
The system changes multiple parameters simultaneously (speed, altitude, route, fuel consumption) to optimize flight trajectories. By varying these parameters based on mission-specific constraints and real-time conditions, the system achieves high adaptability without requiring proportional increases in operational complexity.
2Adaptability or versatility
If conventional systems perform multiple iterations to adjust mission assumptions, then the adaptability improves, but the time consumption increases
Solution Approach 1:
The system performs preliminary calculations of multiple trajectory options and identifies optimal paths in advance, considering various mission criteria and constraints. By pre-calculating and comparing different flight scenarios, the system reduces the need for time-consuming iterative adjustments during actual mission planning.
Solution Approach 2:
The calculation engine uses feedback from mission criteria, weather data, and aircraft performance to continuously refine trajectory recommendations. This iterative feedback mechanism allows the system to converge on optimal solutions more efficiently than conventional step-by-step adjustment methods.
3Ease of operation
If conventional systems follow pre-established flight paths from radio navigation, then the ease of operation is improved, but the manufacturing precision of optimal trajectories deteriorates
Solution Approach 1:
The system replaces traditional radio navigation-based flight paths with computationally optimized trajectories. By substituting automated calculation engines that consider multiple parameters (weather, performance, constraints) for conventional navigation systems, the achievement of precise optimal trajectories is enabled while maintaining ease of operation through automated generation of flight plans.
Data Source
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AI summary
The system includes an aircraft trajectory calculation engine during the mission which includes a trajectory calculation module, designed to calculate a mission trajectory between the geographical origin point (18) and the geographical destination point (20) according to aircraft performance and operational mission specifications. The trajectory calculation module is configured to calculate at least one isochrone curve of the aircraft, including at least one isochrone curve (80) and/or at least one isochrone fuel consumption curve from at least one point (82) of the trajectory and is designed to determine at least one other point (84) of the trajectory on the aircraft isochrone curve.