Helicopter Emergency Landing Gear Deployment Mechanism

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Solution Overview

Problem

Rotary-wing aircraft face challenges in safely landing with a failed landing gear, as existing methods are either risky, damage-prone, or require specialized tools and precision, posing risks to the aircraft and personnel.

Innovation Solution

A rotary-wing aircraft equipped with an emergency landing gear system that includes a main member deployable from a housing to supplement a failed basic landing gear, using an elastic deployment mechanism and holding means to ensure stable support, with optional damping and contact surface features for varied terrain.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of manufacture

If the pilot lands with at least one undercarriage retracted into the fuselage, then the aircraft can land without specialized tools, but this inevitably leads to damage to the fuselage and generates expensive repair costs

Engineering Contradiction:

Improvelanding capabilityVSAvoidfuselage damage

Core Design Contradiction:

Ease of manufactureVSObject-affected harmful factors

Solution Approach 1:

The emergency landing gear is pre-positioned inside the fuselage in a compact stowed configuration. Upon activation, it automatically deploys from the fuselage interior to the exterior landing position, eliminating the need for post-failure tool installation and preventing fuselage damage by providing a ready-to-use landing solution.

Inventive Principle:

Principle #10Preliminary action

Solution Approach 2:

The emergency landing gear acts as an intermediary support structure that bridges the gap between fuselage failure and ground contact. It provides a dedicated landing interface that transfers landing forces away from the fuselage, preventing direct impact damage to the aircraft body.

Inventive Principle:

Principle #24Intermediary (Mediator)

2Object-affected harmful factors

If the pilot lands in a gravel pit dedicated to this purpose, then the landing surface conforms to improve the geometry of the fuselage to limit damage, but this requires specialized landing areas and precise positioning

Engineering Contradiction:

Improvefuselage damageVSAvoidlanding location flexibility

Core Design Contradiction:

Object-affected harmful factorsVSAdaptability or versatility

Solution Approach 1:

The emergency landing gear enables the aircraft to perform its own emergency landing function without requiring external specialized facilities. The system is self-contained within the fuselage and can deploy to any flat surface, eliminating dependence on gravel pits or specialized landing areas while maintaining fuselage protection.

Inventive Principle:

Principle #25Self-service

3Ease of operation

If an operator extends the undercarriage from the outside while hovering close to the ground, then the landing gear can be manually deployed, but this manipulation is risky or even dangerous and is not recommended

Engineering Contradiction:

Improvelanding gear deploymentVSAvoidoperator safety

Core Design Contradiction:

Ease of operationVSReliability

Solution Approach 1:

The emergency landing gear is pre-positioned and pre-configured inside the fuselage before any failure occurs. Upon activation, it automatically deploys from the stowed position to the landing position without requiring operator proximity or manual manipulation, eliminating safety risks while maintaining deployment capability.

Inventive Principle:

Principle #10Preliminary action

4Loss of energy

If the landing gear is retractable to optimize the aerodynamic drag of the aircraft, then the aerodynamic performance is improved, but the landing gear is susceptible to failure such as getting stuck in the undercarriage while in flight inside the fuselage

Engineering Contradiction:

Improveaerodynamic dragVSAvoidlanding gear deployment

Core Design Contradiction:

Loss of energyVSReliability

Solution Approach 1:

The emergency landing gear is pre-positioned in a reliable stowed configuration inside the fuselage that maintains aerodynamic cleanliness. The deployment mechanism is designed with preliminary safety features including manual override capability and unblocking mechanisms that ensure reliable deployment even if the primary automated system fails, addressing both aerodynamic and reliability concerns.

Inventive Principle:

Principle #10Preliminary action

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

Facilitates safe landing by providing emergency support that replaces a failed landing gear, minimizing damage and risk, while ensuring ground stability and adaptability to different landing conditions.

Implementation Method 1

The deployment means comprises an elastic deployment member, such as a spring, acting on the main member to deploy this main member out of a housing

Methodology Applied

Scientific EffectElasticity: Elasticity

Data Source

PatentEP2360093B1Helicopter equipped with emergency landing gear

Publication Date: 2013.05.01 EUROCOPTER FRANCE SA

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AI summary

The present invention relates to a rotary-wing aircraft (1) equipped with an emergency landing gear (10) compensating for a failure of a basic landing gear (2) of the rotary-wing aircraft (1). This emergency landing gear comprises a main component (20) extending from a first end (21) to a second end (22), said emergency landing gear (10) having a deployment means (30) for the main component (20) to deploy this main component (20) out of a housing (3) in order to replace a basic landing gear (2) of a rotary-wing aircraft (1) in the event of a failure, said emergency landing gear (10) being provided with a holding means (40) to lock said main component (20) in position when this main component (20) is deployed out of said housing (3).