Passive Visual Ice Detection Surface for Aircraft Fuselage

Solution Overview

Problem

Existing ice detection systems for aircraft require excitation and measuring circuits to determine the presence of supercooled water droplets above a certain diameter, which is costly and complex, and do not allow for rapid detection without these components.

Innovation Solution

A passive ice detection system for aircraft that uses a visually distinguishable, three-part droplet accumulation surface on the fuselage, with different colored sections to indicate the presence of ice formed by supercooled water droplets of varying diameters, eliminating the need for electronic sensors and circuits.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Device complexity

If passive visual detection surface is used, then device complexity is reduced, but measurement precision may be affected

Engineering Contradiction:

Improvedetection system complexityVSAvoiddroplet detection accuracy

Core Design Contradiction:

Device complexityVSMeasurement precision

Solution Approach 1:

The detection surface is divided into three distinct colored sections (yellow, red, blue) that correspond to different droplet size ranges. Each section is positioned to intercept droplets of specific diameters, allowing the system to differentiate between droplet sizes through visual inspection of which section shows ice accumulation.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The detection surface uses color-coded sections (yellow for small droplets, red for medium droplets, blue for large droplets) to provide immediate visual indication of which droplet size range is present. The color coding allows pilots to quickly identify hazardous conditions without electronic instruments.

Inventive Principle:

Principle #32Color changes

2Ease of operation

If passive visual detection surface is used, then ease of operation is improved, but reliability may be affected

Engineering Contradiction:

Improvedetection operation simplicityVSAvoidice detection reliability

Core Design Contradiction:

Ease of operationVSReliability

Solution Approach 1:

The color-coded sections provide unambiguous visual signals for different droplet size conditions. Yellow indicates small non-hazardous droplets, red indicates medium-sized droplets requiring caution, and blue indicates large hazardous droplets. This color system eliminates interpretation errors and provides reliable operation under various lighting conditions.

Inventive Principle:

Principle #32Color changes

3Ease of manufacture

If electronic sensors and circuits are eliminated, then ease of manufacture is improved, but measurement precision may be affected

Engineering Contradiction:

Improvedetection system manufacturingVSAvoiddroplet size detection accuracy

Core Design Contradiction:

Ease of manufactureVSMeasurement precision

Solution Approach 1:

The detection surface is divided into three distinct colored sections (yellow, red, blue) that correspond to different droplet size ranges. Each section is positioned to intercept droplets of specific diameters, allowing the system to differentiate between droplet sizes through visual inspection of which section shows ice accumulation.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The detection surface uses color-coded sections (yellow for small droplets, red for medium droplets, blue for large droplets) to provide immediate visual indication of which droplet size range is present. The color coding allows pilots to quickly identify hazardous conditions without electronic instruments.

Inventive Principle:

Principle #32Color changes

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 rapid and cost-effective detection of supercooled water droplets by visual inspection, allowing pilots to quickly identify and avoid hazardous ice formation without electronic components, thus improving aircraft safety and reducing complexity.

Implementation Method 1

The airflow in the conduit creates vortices about the sensor. Possessing little motion, the supercooled water droplets below the threshold diameter are unable to penetrate the vortices

Methodology Applied

Scientific EffectVortex flow: Vortex Ring

Implementation Method 2

Supercooled water droplets above the threshold diameter, on the other hand, possess sufficient motion to penetrate the vortices and strike and form ice on the sensor

Methodology Applied

Scientific EffectFreezing: Freezing

Implementation Method 3

a sensor, in particular a vibrating member, housed in a cavity in the casing; and an element for measuring the vibration frequency of the sensor

Methodology Applied

Scientific EffectMechanical vibration: Vibration

Data Source

PatentUS8944383B2Aircraft

Publication Date: 2015.02.03 LEONARDO FINMECCANICA SPA

AI summary

An aircraft having a fuselage and a detecting device for detecting the presence of ice caused by solidification of supercooled liquid droplets having a characteristic dimension above a threshold value. The detecting device has a preferential first portion for accumulating the droplets, and the preferential first portion is located so as to be visible from inside the fuselage.