Integrated Hydraulic Actuator Structure for Lightweight Control Surfaces

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Solution Overview

Problem

Existing aircraft control surfaces and actuators are heavy and bulky, necessitating a need for lighter and more compact designs.

Innovation Solution

Integration of hydraulic actuators into the aircraft control surfaces, forming a unified structure that reduces complexity and weight by eliminating discrete components.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Force

If traditional discrete actuators are used for aircraft control surfaces, then the actuator can provide sufficient force to move the control surface, but the overall assembly becomes heavy and bulky

Engineering Contradiction:

Improveactuator forceVSAvoidcontrol surface assembly weight

Core Design Contradiction:

ForceVSWeight of moving object

Solution Approach 1:

The patent integrates the actuator directly into the control surface structure, merging two previously separate components (actuator and control surface) into a single unified assembly. This eliminates the need for separate mounting structures, fasteners, and intermediate linkages, thereby reducing overall weight while maintaining the required actuator force output.

Inventive Principle:

Principle #5Merging (Combining)

2Reliability

If traditional discrete actuators are used for aircraft control surfaces, then the actuator can perform its function, but the overall assembly becomes bulky and complex

Engineering Contradiction:

Improveactuator functionVSAvoidassembly complexity

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

By integrating the actuator into the control surface, the patent reduces the number of discrete components and interfaces. This merger simplifies the overall assembly structure, reduces the number of potential failure points, and eliminates complex mounting and alignment requirements while preserving the actuator's core function.

Inventive Principle:

Principle #5Merging (Combining)

3Speed

If traditional discrete actuators are used for aircraft control surfaces, then the actuator can move the control surface, but the overall assembly requires more space

Engineering Contradiction:

Improvecontrol surface movementVSAvoidassembly volume

Core Design Contradiction:

SpeedVSVolume of moving object

Solution Approach 1:

The actuator is positioned within or alongside the control surface structure in a nested arrangement, utilizing the existing structural space rather than requiring additional external volume. This nesting approach allows the actuator to operate effectively while minimizing the overall volume of the control surface assembly.

Inventive Principle:

Principle #7Nested doll (Nesting)

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 integration results in a more compact and lightweight aircraft assembly with reduced complexity, enhancing flight performance.

Implementation Method 1

The piston has a first extreme position in which the piston is spaced apart from the piston stop a first distance and a second extreme position in which the piston is spaced apart from the piston stop a second distance

Methodology Applied

Scientific EffectMechanical movement:

Data Source

PatentEP4206072B1Aircraft control surface with integrated hydraulic actuator

Publication Date: 2025.06.25 ROHR INC

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Figure 3A~3B

AI summary

An assembly (20) is provided for an aircraft. This aircraft assembly (20) includes an aircraft control surface (24) and a hydraulic actuator (26). The hydraulic actuator (26) includes a housing (70) and a piston (74) within the housing (70). The housing (70) is formed integral with the aircraft control surface (24).