Variable Thrust Cutback for Aircraft Departure Noise Compliance
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Solution Overview
Problem
Current noise abatement procedures for aircraft departure involve fixed altitudes for thrust cutback and restoration, leading to inefficient fuel usage and inadequate noise reduction, as they do not account for variations in aircraft weight and operating conditions, resulting in suboptimal climb profiles and potential non-compliance with community noise standards.
Innovation Solution
A flight management system that computes a variable thrust cutback during aircraft departure based on real-time sensed altitude and airspeed, using sound exposure level limits and performance data to optimize engine thrust settings, ensuring compliance with noise standards while enhancing fuel efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If fixed altitude thrust cutback procedures are used, then noise reduction is achieved, but fuel efficiency deteriorates due to conservative climb profiles
Solution Approach 1:
The patent applies dynamics by transitioning from fixed altitude thrust cutback to a dynamic system that continuously adjusts thrust based on real-time aircraft state (weight, altitude, airspeed, temperature). The flight management system dynamically computes optimal thrust settings that adapt to changing flight conditions, allowing the aircraft to climb more efficiently while still meeting noise constraints at the specific airport location.
Solution Approach 2:
The patent changes multiple parameters simultaneously - thrust setting, climb rate, and altitude profile - rather than fixing thrust cutback at a single altitude. The system modifies these parameters dynamically based on aircraft weight, environmental conditions, and noise constraints, enabling optimized fuel consumption while maintaining noise compliance.
2Use of energy by moving object
If maximum thrust is maintained for efficient climb, then fuel economy improves, but noise exposure levels exceed community standards
Solution Approach 1:
The patent implements feedback by continuously monitoring aircraft state (altitude, airspeed, weight) and comparing predicted noise exposure against community standards. The flight management system uses this feedback to adjust thrust settings in real-time, maintaining the highest possible thrust that still complies with noise constraints, thereby optimizing fuel economy while ensuring noise compliance.
Solution Approach 2:
The patent applies partial thrust reduction rather than complete cutback at fixed altitudes. By reducing thrust only to the extent necessary to meet noise standards and maintaining higher thrust when conditions permit, the system achieves noise compliance while minimizing the impact on fuel economy and climb performance.
3Object-affected harmful factors
If conservative thrust cutback altitudes are specified, then noise compliance is ensured, but climb time increases and drag losses worsen
Solution Approach 1:
The patent makes the thrust cutback process dynamic rather than static. Instead of prescribing fixed cutback altitudes, the system continuously computes optimal thrust settings based on real-time aircraft state and environmental conditions, allowing the aircraft to reach noise-compliant altitudes more quickly while maintaining compliance throughout the climb.
Solution Approach 2:
The patent maintains continuous thrust adjustment throughout the climb rather than discrete cutback events. The flight management system continuously monitors and adjusts thrust settings, ensuring noise compliance is maintained without unnecessary interruptions to the climb profile, thereby reducing total climb time and drag losses.
4Ease of operation
If fixed thrust cutback procedures are used, then operational simplicity is maintained, but adaptability to different aircraft weights and conditions deteriorates
Solution Approach 1:
The patent makes the system self-service by automatically computing and adjusting thrust settings based on real-time aircraft state without requiring pilot intervention. The flight management system retrieves aircraft weight and environmental data, computes optimal thrust settings, and executes adjustments automatically, maintaining operational simplicity while achieving high adaptability to different flight conditions.
Solution Approach 2:
The patent changes multiple flight parameters (thrust, climb rate, altitude profile) dynamically based on aircraft weight and environmental conditions. This allows a single automated procedure to adapt to diverse flight conditions, maintaining simplicity for the pilot while achieving versatility across different aircraft configurations and environmental scenarios.
Data Source
AI summary
A flight management system is provided for generating a variable thrust cutback during aircraft departure. The flight management system includes memory storing a sound exposure level limit for a navigation flight and storing expected sound exposure levels for an aircraft, and one or more inputs for receiving sensed aircraft variables including altitude and airspeed. The system also includes a processor for processing the sensed altitude and airspeed and stored sound exposure levels. The processor further computes an engine thrust value that complies with the sound exposure level limit based on the altitude, airspeed and the sound exposure levels for controlling aircraft throttle during departure.