Single Actuator Landing Gear Unlocking and Retraction

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Solution Overview

Problem

Existing aircraft landing gear systems require separate actuators for maneuvering and unlocking, necessitating structural modifications for the actuator attachment, which complicates the positioning and retraction process.

Innovation Solution

A method utilizing a single linear or electromechanical actuator coupled between undercarriage elements, transmitting forces through articulation axes, eliminating the need for structural attachment and enabling both unlocking and raising with a single actuator.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Device complexity

If a single actuator is used to provide both maneuvering and unlocking functions, then device complexity is reduced, but the actuator positioning on the undercarriage structure becomes more difficult

Engineering Contradiction:

Improvenumber of actuatorsVSAvoidactuator positioning

Core Design Contradiction:

Device complexityVSEase of manufacture

Solution Approach 1:

The actuator is nested within the existing undercarriage structure by coupling it between the stabilizer member and the leg, utilizing existing structural spaces and attachment points. This allows the actuator to be integrated without requiring external structural modifications, resolving the contradiction between using a single actuator and ease of positioning.

Inventive Principle:

Principle #7Nested doll (Nesting)

Solution Approach 2:

The actuator is designed to perform multiple functions (maneuvering and unlocking) through a single device. By coupling it to both the stabilizer member and the leg, the actuator can simultaneously control the stabilizer's movement and the undercarriage's retraction, eliminating the need for separate actuators while maintaining ease of integration with existing structures.

Inventive Principle:

Principle #6Universality (Multi-functionality)

2Reliability

If separate actuators are used for maneuvering and unlocking, then functional reliability is improved, but device complexity increases

Engineering Contradiction:

Improvefunctional reliabilityVSAvoidnumber of actuators

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The patent merges the maneuvering and unlocking functions into a single actuator. The actuator is coupled to both the stabilizer member and the leg, allowing it to perform both functions through its mechanical connection. This consolidation reduces device complexity while maintaining reliability through the integrated design that ensures both functions are controlled by a single reliable actuator.

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The actuator is designed as a universal component that can perform both maneuvering and unlocking operations. By positioning the actuator to interact with both the stabilizer member and the leg, it achieves multi-functionality, reducing the total number of actuators needed while maintaining the reliability of having dedicated control for each function within a single device.

Inventive Principle:

Principle #6Universality (Multi-functionality)

3Ease of operation

If the actuator is secured to the aircraft structure, then maneuvering control is improved, but structural modifications are required

Engineering Contradiction:

Improvemaneuvering controlVSAvoidstructural modifications

Core Design Contradiction:

Ease of operationVSEase of manufacture

Solution Approach 1:

The actuator is extracted from the aircraft structure and instead coupled directly to the undercarriage components (stabilizer member and leg). This extraction eliminates the need for structural modifications to the aircraft while maintaining effective maneuvering control through direct mechanical coupling to the moving parts of the undercarriage system.

Inventive Principle:

Principle #2Taking out (Extraction)

Solution Approach 2:

The actuator serves as an intermediary between the control system and the undercarriage components. Rather than being secured to the aircraft structure, it couples the stabilizer member and the leg directly, transmitting forces between them to achieve both maneuvering and unlocking functions without requiring any modifications to the aircraft structure.

Inventive Principle:

Principle #24Intermediary (Mediator)

Data Source

PatentEP3495263B1Method of operating an aircraft landing gear between a deployed position and a retracted position

Publication Date: 2022.04.27 SAFRAN LANDING SYSTEMS

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AI summary

The invention relates to a method for maneuvering an aircraft landing gear comprising a movable leg (1) between a deployed position and a retracted position, in which the leg is immobilized by means of a brace (2) held in an aligned position by a stabilizing member (4). The method comprises the use of a maneuvering actuator (10) to raise the leg from the deployed position to the retracted position. According to the invention, the actuator is attached on one side to the leg and on the other side to the stabilizing member such that activation of the actuator first unlocks the stabilizing member and then maneuvers the landing gear leg to the retracted position.