Aircraft Ice Detection Using Density Sensing for Localized Accretion

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Solution Overview

Problem

Conventional ice accretion sensors on aircraft are not capable of detecting localized ice accretion on airfoil surfaces due to their installation on the forward fuselage, which can interfere with airflow and fail to detect ice formation in timely manner, especially in conditions just below freezing.

Innovation Solution

Aircraft ice detection system with multiple detectors positioned at various locations on the aircraft surface, measuring density of collected water and/or ice using depth and mass sensors to generate localized ice accretion signals, enabling efficient activation of targeted ice protection systems.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Measurement precision

If the ice accretion sensor is positioned in the immediate vicinity of the airfoil surface, then the detection capability for localized ice accretion is improved, but the sensor probe would interfere with airflow across the airfoil surface

Engineering Contradiction:

Improveice accretion detection capabilityVSAvoidairflow interference

Core Design Contradiction:

Measurement precisionVSObject-affected harmful factors

Solution Approach 1:

The patent introduces a collection chamber as an intermediary component between the airfoil surface and the sensor probe. The collection chamber receives water and/or ice that impacts the airfoil surface and directs it to the sensor probe, allowing the probe to be positioned away from the airfoil surface while still detecting ice accretion locally. This mediator enables the sensor to detect ice accretion on the airfoil without the probe itself interfering with the airflow over the airfoil surface.

Inventive Principle:

Principle #24Intermediary (Mediator)

2Measurement precision

If the conventional ice accretion sensor is installed on the forward fuselage section, then the sensor can detect ice accretion, but it cannot detect ice accretion localized to different regions of the airfoil surface

Engineering Contradiction:

Improveice accretion detectionVSAvoidlocalized ice accretion information

Core Design Contradiction:

Measurement precisionVSLoss of information

Solution Approach 1:

The patent segments the ice detection system into multiple independent detection points distributed across different regions of the aircraft surface, including the airfoil surface. Each detection point consists of a collection chamber and sensor probe configured to detect ice accretion locally at its position. This segmentation allows the system to detect ice accretion in different regions simultaneously, providing localized information that was lost in the conventional single-point detection system.

Inventive Principle:

Principle #1Segmentation

3Measurement precision

If the conventional ice accretion sensor uses a probe extending beyond the aerodynamic boundary layer, then the sensor can detect ice accretion, but it cannot detect ice formation in timely manner when ambient temperature is just below freezing

Engineering Contradiction:

Improveice accretion detectionVSAvoidice formation detection timing

Core Design Contradiction:

Measurement precisionVSLoss of time

Solution Approach 1:

The patent positions the collection chamber and sensor probe in a location where ice accretion is more likely to form first, such as the leading edge of the airfoil surface. By placing the detection system at this critical location rather than on the forward fuselage, the system can detect ice formation at its earliest stage, providing timely warning before ice accretion spreads to other regions or causes significant aerodynamic degradation.

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

Enables real-time detection and mitigation of localized ice accretion across different regions of the aircraft, improving efficiency by activating ice protection systems only where needed, rather than activating the entire aircraft system.

Implementation Method 1

A depth signal indicating a depth of water and/or ice collected on a baseplate in a collection chamber of an aircraft ice detector is received from a depth sensor

Methodology Applied

Scientific EffectDepth sensing:

Implementation Method 2

A mass signal indicating a mass of the water and/or ice collected on the baseplate is received from a mass sensor

Methodology Applied

Scientific EffectMass measurement:

Implementation Method 3

A density of the water and/or ice collected on the baseplate is calculated based at least on the mass signal and the calculated volume of the water and/or ice collected on the baseplate

Methodology Applied

Scientific EffectDensity measurement:

Data Source

PatentUS20250388329A1Aircraft ice accretion detection based on measuring density

Publication Date: 2025.12.25 THE BOEING CO

AI summary

Examples are disclosed that relate to a method for detecting ice accretion present on an aircraft. In one example, a depth signal indicating a depth of water and/or ice collected on a baseplate in a collection chamber of an aircraft ice detector is received from a depth sensor. A mass signal indicating a mass of the water and/or ice collected on the baseplate is received from a mass sensor. A volume of the water and/or ice collected on the baseplate is calculated based on the depth signal and dimensions of the baseplate. A density of the water and/or ice collected on the baseplate is calculated based on the mass signal and the calculated volume of the water and/or ice collected on the baseplate. An ice accretion signal is output based on the calculated density of the water and/or ice collected on the baseplate being less than a threshold density.