Retractable Vortex Generator for Aircraft Lift Improvement
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Solution Overview
Problem
Flow separation over lifting surfaces, particularly at high angles of attack, leads to increased drag and reduced lift, deteriorating low-speed performance and increasing stall speed, which is problematic during takeoff and landing.
Innovation Solution
A hinged drooped leading edge device coupled with retractable vortex generators that extend into airflow at low speeds to energize the airflow and delay boundary layer separation, while retracting to reduce drag during cruise conditions, mimicking the effect of a complex slotted slat system without its disadvantages.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If heavy complex leading edge high lift devices are used, then low speed performance is improved, but device complexity and weight increase
Solution Approach 1:
The leading edge device is segmented into modular vortex generators that can be independently positioned and adjusted along the leading edge, allowing complex flow control functionality to be achieved through simple, discrete components rather than a single complex mechanism
Solution Approach 2:
The vortex generators are made retractable with adjustable positions, allowing the device to change its geometric parameters (extended vs retracted) to optimize performance for different flight regimes, replacing the need for fixed complex high-lift devices
2Reliability
If vortex generators are extended into airflow, then low speed performance is improved, but drag increases
Solution Approach 1:
The vortex generators are designed to be dynamically extendable and retractable, allowing the system to adapt its configuration based on flight conditions - extended during low-speed operations to improve performance, and retracted during cruise to minimize drag and energy loss
Solution Approach 2:
The vortex generators are periodically deployed and retracted based on flight phase requirements, being extended only when needed for low-speed performance and retracted otherwise to maintain efficient cruise performance
3Reliability
If complex slotted slat system is used, then low speed performance is improved, but maintenance requirements and cost increase
Solution Approach 1:
The patent replaces expensive, complex slotted slat systems with simpler, more economical vortex generators that achieve similar aerodynamic benefits through a different, more manufacturable approach
Solution Approach 2:
The invention extracts the essential flow-control function from the complex slotted slat system and implements it through simpler vortex generators, removing unnecessary complexity while retaining the beneficial aerodynamic effects
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 enhances low-speed performance by reducing stall speed and noise, while maintaining low drag during cruise conditions, replacing heavy and complex leading edge devices with a simpler, lighter, and smoother design.
Implementation Method 1
the vortex generators extend into an airflow. The drooped leading edge increases camber and the extended vortex generators energize the airflow over an upper surface similar to a complex slotted slat system
Data Source
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AI summary
A device and methods for low speed performance improvement of a lifting surface assembly (300) are disclosed. At least one vortex generator (308) is coupled to the lifting surface assembly, and the vortex generator is extended through the lifting surface assembly by drooping a hinged leading edge device (302) coupled to the lifting surface assembly to increase lift. The vortex generator is retracted inside the lifting surface assembly to decrease drag.