Aircraft Ice Detection by Density for Localized Airfoil 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 placement on the forward fuselage, which can lead to delayed detection and inefficient activation of ice protection systems, especially in conditions where ice forms on the leading edge before reaching the sensor.
Innovation Solution
Aircraft ice detectors are positioned at various locations on the airfoil surfaces to measure the density of collected water and/or ice using depth and mass sensors, calculating volume and density to detect ice accretion, enabling localized detection and activation of ice protection systems.
Engineering Contradictions & Design Principles
Engineering 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
Solution Approach 1:
The patent extracts the ice detection function from the traditional probe-based sensor and implements it through a collection chamber system that gathers ice accretion samples and analyzes them in a separate location, eliminating the need for a probe to extend into the airflow path while maintaining detection capability
Solution Approach 2:
The patent introduces an intermediary collection chamber system that acts as a mediator between the airfoil surface and the detection mechanism, allowing ice accretion to be collected and analyzed without the sensor probe directly interfering with the airflow over the airfoil
2Object-generated harmful factors
If the conventional ice accretion sensor is installed on the forward fuselage section, then the sensor placement avoids airflow interference, but the sensor cannot detect localized ice accretion on different regions of the airfoil surface
Solution Approach 1:
The patent segments the ice detection system into multiple independent collection chambers that can be positioned at different locations on the aircraft surface, allowing each chamber to detect ice accretion in its specific region independently, thereby enabling localized detection without requiring a single probe to extend into critical airflow areas
Solution Approach 2:
The patent implements local quality by positioning collection chambers at specific locations where ice accretion is most likely to occur (such as leading edges of airfoils) rather than relying on a single fixed position on the forward fuselage, allowing the system to detect ice accretion characteristics specific to each location
3Loss of time
If the sensor probe is positioned to detect ice accretion early, then the detection timing is improved, but the probe would be in the path of supercooled water droplets that form ice on the leading edge before reaching the sensor
Solution Approach 1:
The patent implements preliminary action by positioning collection chambers at strategic locations where ice accretion begins (such as the leading edge of airfoils) to detect ice formation as it starts, rather than relying on a probe that is positioned downstream and only detects ice after it has already formed and traveled a significant distance
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 efficient and timely detection of ice accretion on aircraft surfaces, allowing for localized mitigation of ice through dedicated ice protection systems, improving operational efficiency and safety.
Implementation Method 1
A mass signal indicating a mass of the water and/or ice collected on the baseplate is received from a mass sensor
Implementation Method 2
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
Data Source
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AI summary
Examples are disclosed that relate to a method (700) for detecting ice accretion present on an aircraft. A depth signal indicating a depth of water and/or ice collected on a baseplate (406) in a collection chamber (402) of an aircraft ice detector is received from a depth sensor (408A). A mass signal indicating a mass of the water and/or ice collected on the baseplate is received from a mass sensor (410). 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.