Aircraft De-icer Tab With Adhesive SLD Sensor

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Solution Overview

Problem

Conventional ice protection systems for aircraft do not adequately protect against supercooled large droplet (SLD) icing conditions aft of the protected region, posing hazards by increasing drag, weight, and decreasing lift, and existing SLD sensors require mechanical attachments that compromise structural integrity and aerodynamic performance.

Innovation Solution

A de-icing assembly featuring a pneumatic de-icer with a tab extending aft from its edge, where a supercooled large droplet sensor is integrated and adhesively attached to the aircraft's outer skin, allowing for detection of SLD icing conditions without modifying the aircraft skin or reducing structural integrity.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If conventional ice protection systems are used, then the leading edge is protected from icing, but the region aft of the de-icer is not protected against SLD ice accumulation

Engineering Contradiction:

Improveice protection coverageVSAvoidice accumulation aft of de-icer

Core Design Contradiction:

ReliabilityVSObject-affected harmful factors

Solution Approach 1:

The sensor is positioned in the chordwise direction aft of the de-icer edge, extending the detection coverage into the previously unprotected region. This dimensional extension allows monitoring of ice accumulation in the gap between the de-icer and the trailing edge, complementing the existing de-icing coverage.

Inventive Principle:

Principle #17Another dimension (Dimensionality change)

2Measurement precision

If existing SLD sensors are mechanically attached to the aircraft skin, then SLD detection is achieved, but the structural integrity and aerodynamic performance are compromised

Engineering Contradiction:

ImproveSLD detection capabilityVSAvoidstructural integrity

Core Design Contradiction:

Measurement precisionVSStrength

Solution Approach 1:

The patent replaces mechanical attachment systems (screws, bolts, brackets) with an adhesive bonding system. The adhesive layer chemically bonds the sensor assembly to the aircraft skin, eliminating mechanical fasteners that would create stress concentration points and potential failure sites, thereby preserving structural integrity while maintaining SLD detection capability.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

Solution Approach 2:

The adhesive layer acts as a thin film that distributes loads uniformly across the bonding interface, preventing stress concentrations that would occur with discrete mechanical fasteners. This thin film approach maintains the aerodynamic smoothness of the surface while providing secure sensor attachment.

Inventive Principle:

Principle #30Flexible shells and thin films

3Measurement precision

If existing SLD sensors are mechanically attached to the aircraft skin, then SLD detection is achieved, but the aerodynamic performance is reduced

Engineering Contradiction:

ImproveSLD detection capabilityVSAvoidaerodynamic performance degradation

Core Design Contradiction:

Measurement precisionVSObject-generated harmful factors

Solution Approach 1:

The adhesive bonding system eliminates the need for mechanical fasteners that would protrude into the airflow or create surface discontinuities. The smooth adhesive bond line maintains aerodynamic flow continuity, preventing turbulence and drag increase that would result from mechanical attachment hardware.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

4Area of stationary object

If the sensor is positioned aft of the de-icer edge, then coverage of unprotected region is improved, but the sensor requires additional attachment structure

Engineering Contradiction:

Improvedetection coverage areaVSAvoidattachment structure

Core Design Contradiction:

Area of stationary objectVSDevice complexity

Solution Approach 1:

The sensor mounting structure is merged with the de-icer assembly itself. The adhesive bonding system attaches both the de-icer and the sensor to the aircraft skin in a single operation, eliminating the need for separate mounting brackets or additional attachment hardware. This integration reduces device complexity while enabling sensor placement in the chordwise direction aft of the de-icer edge.

Inventive Principle:

Principle #5Merging (Combining)

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

The solution effectively detects and alerts pilots to SLD icing conditions, enabling corrective action while maintaining the aircraft's structural and aerodynamic integrity by positioning the sensor aft of the de-icer without additional mechanical attachments or skin modifications.

Implementation Method 1

The de-icer and the tab are adhesively attached onto an outer skin of the airfoil

Methodology Applied

Scientific EffectAdhesive bonding: Adhesive

Data Source

PatentEP3235732B1Pneumatic de-icer with sensor for supercooled large droplet icing detection

Publication Date: 2019.06.12 GOODRICH CORP

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AI summary

A de-icing assembly includes an aircraft (10) with an airfoil (12, 14). A de-icer (32, 132) is disposed on a leading edge of the airfoil. A tab (44, 144) extends from the de-icer in an aft direction from an aft edge of the de-icer. The de-icer and the tab are adhesively attached onto an outer skin (46, 146) of the airfoil. A supercooled large droplet sensor (34, 134) is built into the tab. The supercooled large droplet sensor is positioned in a location aft of the aft edge of the de-icer.