Electric Motor Actuator for Aircraft Trailing Edge

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Solution Overview

Problem

Existing aircraft control systems, particularly those using shape memory alloy actuators, face challenges in quickly and efficiently actuating miniature flaps in both directions, reacting to aerodynamic loads, and preventing flutter due to low stiffness and slow actuation rates.

Innovation Solution

An adaptive trailing edge system utilizing an electric motor actuator coupled with a linkage system to rapidly and differentially actuate adaptive trailing edge elements, providing high stiffness to manage aerodynamic loads and minimize flutter.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of operation

If shape memory alloy actuators are used to deflect miniature flaps, then the flaps can be actuated in a single direction, but the actuation rate is slow and the stiffness is low

Engineering Contradiction:

Improveactuation capabilityVSAvoidactuation rate

Core Design Contradiction:

Ease of operationVSSpeed

Solution Approach 1:

The patent replaces shape memory alloy actuators with an electric motor actuator that drives a screw mechanism. This mechanical substitution enables bidirectional actuation with high speed and high stiffness, resolving the limitations of the shape memory alloy system which could only actuate in one direction with slow speed and low stiffness.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

2Ease of operation

If shape memory alloy actuators are used to deflect miniature flaps, then the flaps can be actuated, but the cooling time required for retraction increases the overall actuation time

Engineering Contradiction:

Improveactuation functionalityVSAvoidretraction time

Core Design Contradiction:

Ease of operationVSLoss of time

Solution Approach 1:

The electric motor actuator with screw mechanism eliminates the thermal cycling requirement of shape memory alloys. The motor can rapidly reverse direction to retract flaps without requiring cooling time, significantly reducing the loss of time associated with actuation cycles.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

3Device complexity

If shape memory alloy actuators are used to actuate miniature flaps, then the system is simple, but the low stiffness makes the actuators incapable of reacting aerodynamic loads and controlling flutter

Engineering Contradiction:

Improveactuator system complexityVSAvoidstiffness

Core Design Contradiction:

Device complexityVSStrength

Solution Approach 1:

The patent replaces the flexible shape memory alloy actuator with a rigid electric motor actuator driving a screw mechanism. This substitution provides high stiffness capable of reacting aerodynamic loads and controlling flutter, while the overall system complexity remains manageable through the use of standard motor and linkage components.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

4Use of energy by moving object

If miniature flaps are deflected during cruise flight to increase lift coefficient, then aerodynamic efficiency is improved, but the ability to quickly retract the flaps during wind shear or high-speed flight is compromised with slow actuators

Engineering Contradiction:

Improveaerodynamic efficiencyVSAvoidretraction speed

Core Design Contradiction:

Use of energy by moving objectVSSpeed

Solution Approach 1:

The electric motor actuator with screw mechanism provides high-speed bidirectional actuation, enabling the system to quickly retract flaps during wind shear or high-speed flight while maintaining the ability to deflect flaps for improved aerodynamic efficiency during cruise flight.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

5Reliability

If miniature flaps are used to maintain airflow attachment at high angles of attack, then stall speed is reduced, but the risk of aerodynamic loading and flutter increases without sufficient actuator stiffness

Engineering Contradiction:

Improveflight safetyVSAvoidaerodynamic loading and flutter

Core Design Contradiction:

ReliabilityVSObject-affected harmful factors

Solution Approach 1:

The rigid electric motor actuator with screw mechanism replaces the flexible shape memory alloy actuator, providing sufficient stiffness to react aerodynamic loads and control flutter while maintaining the safety benefits of miniature flap operation at high angles of attack.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

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

Enables quick retraction and deflection of miniature flaps, improving aerodynamic performance, reducing fuel consumption, and enhancing safety by rapidly adjusting wing load distribution and suppressing aerodynamic-induced vibrations.

Implementation Method 1

An electric motor actuator having an electric motor is configured to actuate the adaptive trailing edge element

Methodology Applied

Scientific EffectElectromagnetic conversion: Electromagnetic Induction

Implementation Method 2

A linkage system couples the electric motor actuator to the adaptive trailing edge element for actuation thereof

Methodology Applied

Scientific EffectMechanical linkage: Lever

Data Source

PatentEP2851287B1Trailing edge actuator system and associated method

Publication Date: 2018.11.07 THE BOEING CO

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AI summary

A trailing edge system for an aircraft may include a trailing edge 202 element mounted to a trailing edge. An electric motor actuator 300 having an electric motor may be configured to actuate the trailing edge element. A linkage system 360 may couple the electric motor actuator to the trailing edge element for actuation thereof.