Elastically Deformable Aircraft Wing Trailing Edge

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Solution Overview

Problem

Traditional aircraft wing assemblies with rigid trailing edges limit the range of motion of flaps, restricting the adjustment of flow turning angles and efficiency, which in turn affects take-off distances and landing speeds.

Innovation Solution

The implementation of elastically deformable trailing edges that bend and flex with the movement of flaps, allowing for a wide range of motion and forming a continuous upper blown surface to enhance lift generation through the Coanda effect.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Adaptability or versatility

If rigid trailing edges are used in traditional aircraft wing assemblies, then structural strength is maintained, but the range of motion of flaps is limited and flow turning efficiency is reduced

Engineering Contradiction:

Improverange of motion of flapsVSAvoidstructural strength of trailing edge

Core Design Contradiction:

Adaptability or versatilityVSStrength

Solution Approach 1:

The trailing edge is designed with elastic deformability, allowing it to dynamically adapt its shape in response to flap movements. The elastic skin and internal structure enable the trailing edge to bend and flex, providing a wide range of motion for the flaps while maintaining structural integrity through controlled deformation.

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The trailing edge incorporates an elastic skin that can deform flexibly to accommodate large flap deflections. This flexible membrane structure allows the trailing edge to conform to various shapes during flap deployment and retraction, significantly increasing the range of motion compared to rigid structures.

Inventive Principle:

Principle #30Flexible shells and thin films

2Adaptability or versatility

If rigid trailing edges are used, then manufacturing simplicity is maintained, but flow turning angle adjustment and efficiency are restricted

Engineering Contradiction:

Improveflow turning angle adjustmentVSAvoidmanufacturing complexity of elastic trailing edge

Core Design Contradiction:

Adaptability or versatilityVSEase of manufacture

Solution Approach 1:

The trailing edge design utilizes changes in material properties and structural parameters to achieve elastic deformability. By selecting appropriate materials and configuring the internal structure, the trailing edge can exhibit controlled elasticity that enables flow turning angle adjustment while remaining manufacturable through conventional aerospace manufacturing processes.

Inventive Principle:

Principle #35Parameter changes

3Productivity

If elastic deformable trailing edges are implemented, then take-off distances are reduced and landing speeds are lowered, but weight increases

Engineering Contradiction:

Improvetake-off distance and landing speed performanceVSAvoidweight of trailing edge assembly

Core Design Contradiction:

ProductivityVSWeight of moving object

Solution Approach 1:

The use of thin elastic skin membranes allows the trailing edge to achieve the required deformability with minimal material usage. This flexible shell structure provides the necessary elasticity for improved take-off and landing performance while keeping the added weight to a minimum compared to heavier rigid alternative structures.

Inventive Principle:

Principle #30Flexible shells and thin films

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 design enables shorter take-off distances, lower landing speeds, reduced weight, and increased fuel volume capacity by optimizing flow turning angles and efficiency during different phases of flight.

Implementation Method 1

The trailing edge has an elastically deformable skin defining a first surface. The skin is to elastically deform when the second end of the trailing edge moves relative to the first end of the trailing edge.

Methodology Applied

Scientific EffectElasticity: Elasticity

Implementation Method 2

the efflux of the engines interacts with upper surfaces of the wings and the flaps to provide lift. For example, the efflux may follow a curvature of the upper surfaces of the wings and the flaps to provide lift.

Methodology Applied

Scientific EffectCoanda effect: Coanda Effect

Data Source

PatentUS11117647B2Aircraft wing assemblies

Publication Date: 2021.09.14 THE BOEING CO

AI summary

Aircraft wing assemblies are disclosed herein. An example apparatus disclosed herein includes a trailing edge of a wing of an aircraft. The trailing edge has an elastically deformable skin defining a first surface. The trailing edge has a first end to be fixed to the wing and a second end opposite the first end that is to move relative to the first end. A flap is movably coupled to the second end of the trailing edge. The flap is movable between a stowed position and a deployed position. The trailing edge is to elastically elongate when the flap moves from the stowed position to the deployed position and the trailing edge is to elastically collapse when the flap moves from the deployed position to the stowed position.