Aircraft Descent Profile Control With Dynamic Guidance Segmentation
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Solution Overview
Problem
Current flight management systems (FMS) are limited by outdated programming techniques that assume constant aircraft performance characteristics during descent, failing to optimize for speed, time, and cost constraints, leading to suboptimal descent profiles.
Innovation Solution
A method and system that utilize nonlinear programming to define a descent profile with two segments: an optimal guidance trajectory for the initial segment and position-based guidance for the second segment, optimizing fuel consumption and reducing costs by dynamically adjusting aircraft parameters like airspeed and thrust.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If constant aircraft performance characteristics are assumed during descent, then the programming is simpler and compatible with prior generation systems, but fuel consumption is not optimized and operational costs increase
Solution Approach 1:
The patent applies dynamics by transitioning from static, constant performance assumptions to dynamic, real-time performance modeling. The system continuously updates aircraft performance characteristics based on actual flight conditions, enabling optimal descent profile calculation that adapts to changing weights, atmospheric conditions, and aircraft state, thereby reducing fuel consumption while maintaining computational feasibility through efficient algorithms.
Solution Approach 2:
The patent implements parameter changes by varying key descent parameters such as airspeed, thrust, and descent rate based on real-time aircraft performance data. Instead of maintaining constant values, the system dynamically adjusts these parameters throughout the descent to optimize fuel efficiency while satisfying operational constraints, representing a fundamental shift from fixed-parameter to variable-parameter control.
2Device complexity
If constant airspeed or Mach is maintained during descent, then the control system is simpler, but speed and time constraints cannot be optimized
Solution Approach 1:
The system employs dynamic speed management where the optimal airspeed or Mach number is continuously calculated and updated throughout the descent based on changing aircraft weight, atmospheric conditions, and operational constraints. This dynamic approach enables the system to satisfy both speed constraints and time constraints simultaneously, achieving superior descent optimization compared to constant speed methods while managing complexity through efficient real-time computation.
3Ease of operation
If pre-defined constant values are used for aircraft performance parameters, then the flight management system is easier to operate, but accurate fuel consumption optimization cannot be achieved
Solution Approach 1:
The system implements self-service by automatically calculating and updating optimal descent profiles using real-time aircraft performance data without requiring manual intervention. The flight management system independently processes current aircraft state, weight, and environmental conditions to generate optimized descent trajectories, maintaining ease of operation while achieving high precision in fuel consumption optimization through continuous self-updating performance models.
4Stability of the object's composition
If outdated programming techniques are used in flight management systems, then compatibility with prior generation systems is maintained, but cost optimization capabilities are limited
Solution Approach 1:
The patent applies segmentation by dividing the descent profile into multiple phases or segments, each with its own optimization criteria and control strategies. This segmented approach allows the system to maintain compatibility with existing flight management systems while implementing advanced optimization techniques in specific descent phases, thereby achieving cost optimization without requiring complete system replacement.
Data Source
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AI summary
A method (100) and system of operating a vehicle in a descent profile (16), the method (100) comprising obtaining (102), at a controller module (32), a mathematical model of performance characteristics for an aircraft (20), generating (104) an optimal guidance trajectory, and operating (106) the aircraft (20) in accordance with the optimal guidance trajectory prior to operating in a position-based guidance.