Aircraft Wing Tip Stall Trigger System
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Solution Overview
Problem
Current stall trigger systems for aircraft wing tips lack the ability to dynamically control airflow separation in response to varying flight parameters, leading to inefficient drag management and sudden flow separation at high incidences.
Innovation Solution
A stall trigger system comprising multiple sets of triggers with different activation thresholds, distributed along the span of an aircraft wing tip, which are activated in a sequence by a control system monitoring parameters like angle of incidence or pressure to trigger local airflow separation, thereby emulating the behavior of a highly swept winglet and reducing drag.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a single stall trigger is used at the wing tip, then the structure is simple, but the airflow separation cannot be dynamically controlled and drag management is inefficient
Solution Approach 1:
The wing tip is divided into multiple discrete trigger locations along the span, with each trigger independently controllable. This segmentation allows different portions of the wing tip to be activated at different angles of incidence, enabling dynamic control of airflow separation patterns while managing drag efficiently.
Solution Approach 2:
The system transitions from a static single-trigger design to a dynamic multi-trigger system where triggers are activated sequentially based on real-time angle of incidence measurements. This dynamic activation pattern allows the system to adapt to varying flight conditions and optimize drag management throughout the flight envelope.
2Ease of operation
If stall triggers are activated suddenly at high incidence, then the structure is simple, but sudden flow separation occurs causing poor handling qualities
Solution Approach 1:
Multiple stall triggers are positioned at different spanwise locations with different activation thresholds. As the angle of incidence increases, triggers are activated sequentially from the outermost spanwise location inward, creating a progressive flow separation pattern. This preliminary sequential activation prevents sudden flow separation and maintains smoother handling characteristics.
Solution Approach 2:
The control system continuously monitors the angle of incidence and uses this feedback to determine which triggers should be activated. This feedback mechanism ensures that triggers are activated in the correct sequence based on actual flight conditions, preventing sudden stalls and maintaining predictable aircraft behavior throughout the maneuver.
3Adaptability or versatility
If multiple stall triggers with different activation thresholds are used, then airflow separation can be dynamically controlled, but the device complexity increases
Solution Approach 1:
Different trigger sets are positioned at different spanwise locations and have different activation thresholds tailored to their specific locations. This local differentiation allows each trigger to contribute optimally to drag management in its specific region, with outer triggers activating at lower incidences and inner triggers activating at higher incidences, creating an optimized overall drag characteristic.
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
The system effectively manages airflow separation, reducing drag and improving handling qualities by triggering local separation in a controlled sequence, avoiding sudden stalls and maintaining efficient lift across a wider range of incidences.
Implementation Method 1
each set of stall triggers comprises one or more stall triggers which can be activated to trigger local separation of air flow over the aircraft wing tip or aircraft wing tip device
Data Source
AI summary
A stall trigger system is disclosed having an aircraft wing tip or aircraft wing tip device, a plurality of sets of stall triggers distributed along a span of the aircraft wing tip or aircraft wing tip device. Each set of stall triggers comprises one or more stall triggers which can be activated to trigger local separation of air flow over the aircraft wing tip or aircraft wing tip device, and each set of stall triggers has a different activation threshold. A control system configured to monitor a parameter, and activate each set of stall triggers in response to the parameter reaching its respective activation threshold.