Active Winglet Attitude Control for Fuel Burn Drag Changes
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Solution Overview
Problem
Aircraft attitude changes due to mass reduction and distribution variations during flight, leading to increased drag and fuel consumption, as fuel is consumed and redistributed within the aircraft, necessitating effective control mechanisms to maintain optimal lift and drag conditions.
Innovation Solution
An aircraft attitude controller that actively controls the position of a winglet to adjust the angle of incidence, thereby managing the center of lift and reducing drag by dynamically changing the lift distribution over the wing, eliminating the need for fuel ballast systems and simplifying aircraft design.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If fuel is consumed during flight, then mass of the aircraft decreases, but attitude of the aircraft changes leading to increased drag
Solution Approach 1:
The winglet is designed to be movable relative to the wing portion, allowing its position to be dynamically adjusted during flight. The attitude controller actively changes the winglet position in response to detected attitude changes, enabling the winglet to adapt to varying flight conditions and mass distribution as fuel is consumed, thereby maintaining optimal aerodynamic performance and reducing drag.
Solution Approach 2:
The system changes the physical parameter of the winglet's position and angle of incidence to compensate for attitude changes. By adjusting the winglet position, the system modifies the lift distribution on the wing, which counteracts the attitude changes that would otherwise increase drag, thus maintaining efficient flight conditions throughout the flight.
2Stability of the object's composition
If fuel distribution changes during flight, then centre of gravity moves, but attitude control requires complex fuel ballast systems
Solution Approach 1:
The invention extracts the attitude control function from the fuel ballast system. Instead of using complex pumps and pipes to move fuel for attitude control, the system uses a separate movable winglet mechanism that is controlled independently based on attitude detection, thereby eliminating the need for complex fuel ballast systems while still achieving attitude control.
Solution Approach 2:
The winglet serves multiple functions: it provides lift enhancement, controls attitude by adjusting lift distribution, and reduces drag. This multi-functional design eliminates the need for separate fuel ballast systems dedicated to attitude control, simplifying the overall aircraft system while maintaining stability control capabilities.
3Productivity
If winglet position is actively controlled, then attitude is maintained optimally, but device complexity increases
Solution Approach 1:
The attitude controller operates as a feedback control system that detects the aircraft's attitude and automatically adjusts the winglet position accordingly. This closed-loop control maintains optimal attitude and flight efficiency without requiring complex manual intervention or overly complicated control mechanisms, as the system self-regulates based on real-time attitude information.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This solution reduces fuel consumption, minimizes drag, and enhances flight efficiency by maintaining optimal attitudes without altering fuel distribution, allowing for shorter takeoff and landing distances and reduced operational complexity.
Implementation Method 1
Aerodynamic heating may occur during flight of the aircraft. This may be due to friction between air and the aircraft, and/or due to compression of air in front of the aircraft.
Implementation Method 2
Aerodynamic heating may occur during flight of the aircraft. This may be due to friction between air and the aircraft, and/or due to compression of air in front of the aircraft.
Data Source
Figure 1A~1B
Figure 2~3B
Figure 4~5
AI summary
Disclosed is an aircraft attitude controller configured to obtain information representative of an attitude of an aircraft and, on the basis of the information, control the attitude of the aircraft by actively controlling a position of a winglet at a distal end of a wing portion of a wing of the aircraft, relative to the wing portion, thereby to control an angle of incidence of the winglet.