Dynamic Departure Profile Generation for Noise and Fuel Optimization
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Solution Overview
Problem
Existing aircraft departure profile systems are 'one-size-fits-all' and do not consider specific aircraft types, ambient conditions, or payload, leading to inefficient fuel use and potential noise abatement limit violations, as they focus solely on worst-case scenarios for thrust, climb, and speed without accounting for factors like fuel efficiency or other aircraft operations.
Innovation Solution
A system comprising a flight performance data generator and a comparison module that calculates departure performance data based on current conditions and desired profiles, comparing external criteria such as noise levels to ensure compliance with emission limits, allowing for adjustments to optimize departure profiles for each flight, reducing noise and fuel consumption.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If a one-size-fits-all departure profile is used for all aircraft, then noise abatement limits are ensured to be met, but fuel efficiency deteriorates and unnecessary compliance margins are created
Solution Approach 1:
The patent applies local quality by tailoring departure profiles to specific aircraft types, ambient conditions, and payloads rather than using a uniform approach. The system calculates customized thrust, climb, and speed parameters for each aircraft based on its unique characteristics and operating conditions, thereby optimizing fuel efficiency while maintaining noise abatement compliance.
Solution Approach 2:
The patent implements dynamics by making departure profiles adaptive and variable rather than static. The system dynamically adjusts profile parameters based on real-time conditions including aircraft type, ambient temperature, pressure, and payload weight, allowing optimal performance across different operating scenarios while meeting noise limits.
2Reliability
If worst-case scenarios are used for thrust, climb, and speed calculations, then safety is ensured and noise limits are met, but fuel efficiency and operational performance deteriorate
Solution Approach 1:
The patent applies parameter changes by modifying thrust, climb, and speed parameters based on actual aircraft conditions rather than fixed worst-case values. The system calculates optimized parameters that maintain safety margins while reducing excessive fuel consumption associated with conservative worst-case assumptions.
Solution Approach 2:
The patent implements feedback by continuously monitoring actual aircraft performance and ambient conditions, then adjusting departure profile parameters accordingly. This closed-loop approach ensures safety requirements are met while optimizing fuel efficiency based on real-time data rather than static worst-case assumptions.
3Device complexity
If a single departure profile is applied to all aircraft types and conditions, then system complexity is minimized, but adaptability and precision in meeting noise limits deteriorate
Solution Approach 1:
The patent applies universality by creating a multi-functional departure profile generation system that handles various aircraft types, ambient conditions, and operational scenarios through a unified computational framework. The system uses universal calculation methods that adapt to specific conditions, providing both broad applicability and precise customization.
Data Source
AI summary
Systems and methods are described for dynamically generating flight departure profiles that are in compliance with aircraft emission limits. Emission limits may include noise abatement limits. Flight departure profiles may be generated on a flight by flight basis, and/or may be based on then-current conditions such as wind speed, wind direction, and ambient temperature.