Aircraft Wing Foldable Tip Actuation Linkage

Resolve Bottlenecks,
Find Innovative SolutionsGenerate Solutions

Solution Overview

Problem

Existing aircraft wing designs with foldable wing tips face challenges in reducing complexity and weight of the actuation unit while ensuring reliable movement between extended and folded positions, which affects the overall aircraft's space requirements and cost efficiency.

Innovation Solution

A four-bar-linkage mechanism is employed, comprising a first link element connected to the actuation unit and a second link element coupled to the foldable wing tip via a third hinge, allowing for reduced actuator loads and downsizing of the actuation unit, with specific hinge and link configurations optimizing kinematics for efficient movement.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If a traditional actuation unit design is used to move the foldable wing tip portion, then the wing tip can be reliably moved between extended and folded positions, but the actuation unit has high weight and complexity

Engineering Contradiction:

Improvereliability of movement between extended and folded positionsVSAvoidcomplexity of actuation unit

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The actuation system is segmented into a four-bar linkage mechanism with multiple independent link elements (first link element, second link element, third link element) connected through hinges. This segmentation distributes the actuation function across multiple simple components rather than requiring a single complex actuator, thereby reducing overall device complexity while maintaining reliability through the coordinated action of the linkage.

Inventive Principle:

Principle #1Segmentation

2Reliability

Engineering Contradiction:

Improvereliability of movement between extended and folded positionsVSAvoidweight of actuation unit

Core Design Contradiction:

ReliabilityVSWeight of moving object

Solution Approach 1:

The patent replaces a traditional direct-drive actuation system with a mechanical linkage system (four-bar mechanism) that uses geometric relationships and leverage to achieve the folding motion. This substitution allows the use of lighter components that rely on mechanical advantage rather than requiring a heavy, high-torque actuator, thereby reducing the weight of the moving actuation unit while maintaining reliable movement capability.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

3Device complexity

If the actuation unit is downsized to reduce weight and complexity, then cost is reduced, but the ability to reliably move the wing tip may be compromised

Engineering Contradiction:

Improvecomplexity of actuation unitVSAvoidreliability of movement between extended and folded positions

Core Design Contradiction:

Device complexityVSReliability

Solution Approach 1:

The four-bar linkage is designed with specific hinge positions and link dimensions that create favorable dynamic characteristics during the folding motion. The linkage geometry is optimized so that the actuation forces naturally align with the motion requirements, providing mechanical advantage throughout the range of motion. This dynamic optimization ensures that even downsized actuator components can reliably move the wing tip through the extended and folded positions without compromising reliability.

Inventive Principle:

Principle #15Dynamics

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 four-bar-linkage design minimizes actuator loads and unit complexity, enabling efficient folding and extension of the wing tip with reduced weight and cost, thereby optimizing aircraft space requirements during maneuvering and parking.

Implementation Method 1

a four-bar-linkage, which relates to a particularly advantageous kinematics for transferring actuation loads to the foldable wing tip portion

Methodology Applied

Scientific EffectMechanical Advantage: Mechanical Advantage

Implementation Method 2

the first link element is fixedly mounted with its first end to a rotatable output, preferably to a rotatable output shaft, of the actuation unit and is rotatably coupled with its opposite second end to a first end of the second link element via a second hinge spaced from the output

Methodology Applied

Scientific EffectRotation:

Data Source

PatentUS11440638B2Wing for an aircraft

Publication Date: 2022.09.13 AIRBUS OPERATIONS GMBH

AI summary

A wing (3) for an aircraft (1) including a fixed wing (5), a foldable wing tip portion (9) mounted to the fixed wing (5) via a first hinge (11) rotatable about a first hinge axis (13) between an extended position (15) and a folded position (17), and an actuation unit (19) arranged at the fixed wing (5) and coupled to the foldable wing tip portion (9) via a linkage (21) including a first link element (23) and a second link element (25), wherein the first link element (23) is mounted to a rotatable output (27) of the actuation unit (19) and is rotatably coupled to the second link element (25) via a second hinge (29), and wherein the second link element (25) is rotatably coupled to the foldable wing tip portion (9) via a third hinge (31).