Aircraft Flap Control System for Optimized Takeoff Performance
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Solution Overview
Problem
Conventional aircraft systems lack the ability to optimize flap settings and thrust settings based on specific aircraft configurations and environmental conditions, leading to inefficient engine operation, excessive engine wear, and suboptimal climb rates.
Innovation Solution
A system comprising a flight control computer that computes an optimum flap setting and thrust setting using aircraft and airport data, including a flap control system with a variable-trailing-edge-position switch to adjust trailing edge devices, allowing for precise control of flap positions and thrust levels.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If conventional fixed flap settings are used, then the aircraft can operate with simple control systems, but the engine must operate at unnecessarily high thrust settings leading to increased engine wear and fuel consumption
Solution Approach 1:
The patent implements a dynamic flap positioning system that continuously adjusts flap deflection angles based on real-time flight conditions, aircraft weight, and performance requirements. This replaces static conventional flap settings with adaptive control, allowing the system to optimize fuel efficiency while maintaining operational simplicity through automated control.
Solution Approach 2:
The system varies flap deflection parameters continuously rather than using fixed discrete settings. By changing flap angle parameters dynamically based on flight phase, weight, and performance targets, the system achieves fuel optimization without requiring complex manual intervention from pilots.
2Device complexity
If conventional fixed flap settings are used, then the control system remains simple, but the climb rate may be above or below requirements for obstacle or engine-out climb performance
Solution Approach 1:
The patent incorporates feedback control mechanisms that continuously monitor flight conditions, performance metrics, and environmental factors. The system uses this feedback to automatically adjust flap settings, ensuring climb performance meets safety requirements while maintaining controlled system complexity through structured control algorithms.
3Loss of energy
If flap settings are optimized for reduced thrust, then engine wear and fuel burn are reduced, but the system requires complex computation and control mechanisms
Solution Approach 1:
The system performs preliminary computations of optimal flap settings during flight planning and pre-flight preparation. By calculating optimal configurations in advance based on forecast conditions and aircraft weight, the system reduces real-time computational requirements while achieving fuel optimization benefits.
4Weight of moving object
If precise flap positioning is implemented, then takeoff weight capability increases, but the control system requires higher precision and more components
Solution Approach 1:
The patent replaces traditional mechanical flap positioning systems with electro-hydrostatic or electro-mechanical actuators that offer precise control through electronic signals. This substitution enables fine-grained adjustment of flap angles to optimize lift and drag characteristics, increasing takeoff weight capability while maintaining manageable system complexity through electronic control.
Data Source
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AI summary
A system (180) for optimizing performance of an aircraft (100) may include a flight control computer (182) for computing an optimum flap setting (184) based on aircraft data (400). The system (180) may further include a flap control system (198) having a flap control device (200). The system (180) may additionally include a flap actuation system (174) coupled to the flap control system (198) for positioning the trailing edge device (150) at the optimum flap setting (184).