Aircraft Window Ice Accretion Boundary Locator
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Solution Overview
Problem
Ice formation on aircraft surfaces increases weight and drag, affects lift and thrust, and reduces controllability, making existing detection methods inadequate for predicting and managing ice accretion effectively.
Innovation Solution
A system that projects light beams onto an aircraft window to detect ice accretion by determining test locations based on flight conditions and super-cooled water droplet sizes, using an optical detector to compare reflected light with thresholds and generate alerts, and includes a heater for de-icing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If existing detection methods are used to monitor ice formation, then the system complexity is low, but the measurement precision and reliability of ice accretion detection are insufficient
Solution Approach 1:
The patent uses an optical intermediary (light beam) to indirectly detect ice accretion on the aircraft surface. The optical detector monitors changes in light reflection properties caused by ice formation, providing precise measurement without requiring direct contact with the ice-covered surface. This intermediary approach enables high-precision detection while keeping the overall system relatively simple.
Solution Approach 2:
The patent replaces traditional mechanical or visual inspection methods with an optical detection system. Instead of using physical sensors that would require direct contact with the aircraft surface or relying on pilot visual inspection through cockpit windows, the system uses optical beams and detectors to non-contactingly measure ice accretion, thereby improving measurement precision.
2Measurement precision
If visual inspection by pilot is used to detect ice formation, then the device complexity is minimal, but the measurement precision and coverage are limited
Solution Approach 1:
The system employs an optical intermediary to extend the pilot's visual capability. The optical detector captures light reflected from the aircraft surface, and the boundary locator processes this optical information to precisely identify ice accretion boundaries, providing measurement precision far beyond human visual capabilities while maintaining a relatively simple system architecture.
Solution Approach 2:
The optical detection system creates an optical copy or representation of the aircraft surface condition. By analyzing the reflected light patterns, the system generates information about ice accretion that mirrors the actual physical state, enabling precise detection without requiring the pilot to directly view the affected surfaces.
3Reliability
If comprehensive atmospheric monitoring is implemented to predict ice formation, then the reliability of ice prediction improves, but the device complexity and energy consumption increase
Solution Approach 1:
The system performs preliminary detection of ice accretion boundaries before significant ice formation occurs. By continuously monitoring the aircraft surface with optical beams and identifying boundary conditions, the system can predict impending ice formation and alert the pilot in advance, improving prediction reliability without requiring complex atmospheric sensing equipment.
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
Effectively monitors and manages ice accretion on aircraft surfaces by accurately detecting ice formation, reducing the risk of weight and drag increases, and maintaining aircraft performance and safety.
Implementation Method 1
an optical detector configured to detect a portion of the projected beam of light reflected by the aircraft window
Implementation Method 2
a heater configured to heat the aircraft window so as to melt, evaporate, and/or sublimate any ice accreted thereto
Implementation Method 3
a heater configured to heat the aircraft window so as to melt, evaporate, and/or sublimate any ice accreted thereto
Implementation Method 4
a heater configured to heat the aircraft window so as to melt, evaporate, and/or sublimate any ice accreted thereto
Data Source
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AI summary
Apparatus and associated methods relate to projecting a light beam onto an interior surface of an aircraft window (20) so as to indicate a testing location (21) to test for ice accretion. The testing location (21) is determined, by a boundary locator (14), based on aircraft flight conditions, aircraft exterior shape, and a predetermined size of super-cooled droplets, which could present a hazard to the aircraft. The determined test location (21) corresponds to a calculated boundary that separates locations where super-cooled water droplets of the predetermined size cause ice-accretion from locations where such particles do not cause ice accretion, for such aircraft flight conditions. The light beam is then projected onto the interior surface of the aircraft window (20) at the determined test location (21). The projected beam of light can indicate, to an observer and/or a detector, a location to monitor for ice accretion caused by super-cooled water droplets of the predetermined size.