Wingtip Flow Interruption for Transverse Load Relief
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing aircraft winglets are designed to handle extreme flight conditions, leading to additional structural reinforcement and weight, which detracts from efficiency gains and increases dynamic loads, particularly during infrequent events like sideslip maneuvers or lateral gusts.
Innovation Solution
A flow interrupting device is attached to the wingtip device, causing a flow to separate at a desired angle of attack, reducing stresses and loads by disrupting the boundary layer and minimizing structural reinforcement needs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If winglets are designed to handle extreme flight conditions with additional structure, then reliability is improved, but weight increases and efficiency is reduced
Solution Approach 1:
The patent changes the aerodynamic parameters by introducing a flow interrupting device that modifies the flow regime over the winglet. This creates a controlled separation bubble that reduces the effective angle of attack on the winglet during extreme conditions, thereby reducing loads without requiring additional structural reinforcement.
Solution Approach 2:
The flow interrupting device acts as an intermediary element between the freestream flow and the winglet surface. It introduces a controlled separation that mediates the interaction between the flow and the winglet, reducing the direct aerodynamic loading on the structure during extreme flight conditions.
2Strength
If additional structure is added to handle extreme loads, then strength is improved, but device complexity increases
Solution Approach 1:
Instead of changing the structural parameters of the winglet, the patent changes the aerodynamic parameters by introducing flow separation. This reduces the effective loads on the existing structure, allowing the same structure to handle extreme conditions without additional reinforcement.
Solution Approach 2:
The patent extracts the load reduction function from the structural design and places it in the aerodynamic design. Rather than making the winglet stronger through additional structure, the load reduction is achieved through aerodynamic means by creating a controlled separation bubble.
3Reliability
If winglets are designed for extreme conditions, then reliability is improved, but efficiency is reduced due to increased weight
Solution Approach 1:
The patent changes the aerodynamic parameters during extreme conditions by inducing flow separation, which reduces the effective angle of attack and loads on the winglet. This allows the aircraft to maintain efficiency during normal operation while achieving reliable performance during extreme conditions without the penalty of additional weight.
Solution Approach 2:
The flow interrupting device creates a dynamic flow separation that adapts to flight conditions. During extreme conditions, the separation bubble forms and reduces loads, while during normal operation, the flow remains attached and the winglet operates at full efficiency, providing a dynamic response to varying flight conditions.
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
Reduces structural stress and weight on the aircraft by selectively managing loads during transverse flows, improving efficiency and reducing drag losses.
Implementation Method 1
the edge extended into the boundary layer may disrupt (or interrupt) the boundary layer and cause a flow to separate from the wingtip device
Implementation Method 2
causing a flow to separate from a wingtip device at a desired angle of attack
Data Source
AI summary
A flow interrupting device may cause a flow to separate from a wingtip device at a desired angle of attack. The flow interrupting device may be coupled to a leading edge of a wingtip device where a flow disruptor may be configured to alleviate a load on the wingtip device. The flow disrupter may comprise an edge that extends into a boundary layer at a threshold angle of attack that may disrupt the boundary layer and cause a flow to separate from the wingtip device. This separated flow may reduce stresses experienced by the wingtip device and wing during various flight conditions where a transverse flow is encountered.