Leading Edge Variable Camber System for Aircraft Drag Reduction
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Solution Overview
Problem
Conventional aircraft systems face challenges in dynamically adjusting wing camber during different phases of flight, leading to increased structural weight and aerodynamic drag, which affects fuel efficiency and payload capacity.
Innovation Solution
A variable camber system that includes leading edge devices, such as slats, actuated by a slat actuation system to adjust upwardly and downwardly relative to a retracted position, allowing for dynamic adjustment of wing camber, optimized through a flight control computer that computes settings based on aircraft state data to minimize drag and structural weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If trailing edge flaps are extended to increase wing camber for increased lift, then lift capability is improved, but aerodynamic drag increases
Solution Approach 1:
The leading edge device is made dynamically adjustable through an actuation system that can change its position between retracted and extended states, allowing the wing camber to be optimized for different flight phases. This dynamic adjustment enables the aircraft to reduce drag during cruise by retracting the device and increase lift during takeoff/landing by extending it.
2Ease of operation
If trailing edge flaps are made extendable by fixed increments, then ease of operation is improved, but adaptability to different flight conditions deteriorates
Solution Approach 1:
The system transitions from static fixed-increment flap settings to dynamic continuous adjustment capability. The leading edge device can be positioned at various degrees of extension based on real-time flight conditions, enabling continuous optimization of wing camber rather than discrete fixed settings.
Solution Approach 2:
The control system receives aircraft state data and automatically commands the leading edge device to appropriate positions. This closed-loop feedback mechanism allows the system to adapt to changing flight conditions automatically, improving both ease of operation and adaptability simultaneously.
3Loss of energy
If trailing edge flaps are retracted at cruising altitude to avoid drag penalty, then aerodynamic efficiency is improved, but lift capability deteriorates
Solution Approach 1:
The leading edge device provides dynamic camber adjustment capability that allows the aircraft to maintain optimal aerodynamic efficiency at cruising altitude with the device retracted, while rapidly transitioning to high lift capability when needed for descent, approach, or landing configurations.
4Strength
If wing structure is strengthened to handle higher loads from extended flaps, then structural strength is improved, but aircraft weight increases
Solution Approach 1:
By making the leading edge device dynamically adjustable rather than permanently extended, the wing structure can be optimized for a balance between strength and weight. The structure only needs to handle the maximum expected loads during specific flight phases, not continuous high loads, reducing the required structural weight while maintaining safety.
Data Source
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AI summary
A system for varying a wing camber of an aircraft wing may include a leading edge device 152 coupled to the wing. The leading edge device may be configured to be actuated in an upward direction 166 and a downward direction 168 relative to a retracted position 158 of the leading edge device.