Aircraft Control Surface Closed-Loop Drag Optimization
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Solution Overview
Problem
Existing aircraft control surface adjustment systems rely on pre-defined tables that do not account for instantaneous aircraft conditions, leading to suboptimal drag reduction during flight, which affects fuel efficiency and emissions.
Innovation Solution
A closed-loop control system that measures flight metrics, uses a processor to calculate optimal control surface angles based on current conditions, and adjusts the surfaces to minimize drag, incorporating a Kalman-filter based method and table lookup data to estimate sensitivity and optimize deflections.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If pre-defined tables are used to adjust control surfaces, then the system is simple to operate, but drag reduction is suboptimal because instantaneous aircraft conditions are not accounted for
Solution Approach 1:
The patent implements a closed-loop feedback system that continuously measures flight metrics (altitude, Mach number, weight, center of gravity, vertical speed) and uses this real-time data to dynamically adjust control surface positions. This feedback mechanism enables the system to account for instantaneous aircraft conditions and optimize drag reduction, resolving the contradiction between operational simplicity and energy efficiency.
Solution Approach 2:
The system transitions from static pre-defined tables to dynamic real-time optimization by continuously adjusting control surface positions based on current flight conditions. The dynamic adjustment allows the aircraft to adapt to changing conditions during flight, improving drag reduction performance while maintaining ease of operation through automated control.
2Loss of energy
If real-time optimization is implemented to reduce drag, then fuel efficiency improves, but system complexity increases
Solution Approach 1:
The patent leverages the existing flight control system and available flight metrics sensors to implement drag optimization, avoiding the need for completely new dedicated hardware. By utilizing multi-functional existing components and data sources, the system achieves real-time optimization while minimizing additional system complexity.
3Loss of energy
If control surfaces are dynamically adjusted based on flight conditions, then drag coefficient is reduced, but measurement and control precision requirements increase
Solution Approach 1:
The patent introduces a dynamic adjustment control module that acts as an intermediary between existing flight metrics sensors and the flight control system. This module processes available flight data and generates optimized control surface commands, enabling drag reduction without requiring direct enhancement of measurement precision infrastructure.
Data Source
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AI summary
Closed loop control method for control surfaces includes measuring a flight metric of an aircraft during flight and calculating, using a processor, a deflection of a control surface of the aircraft based on the flight metric. The disclosed method also includes adjusting the deflection to an effective deflection level based on the calculated deflection to reduce a drag coefficient of the aircraft.