Carbon Composite Propeller De-Icing With Distributed Blade Heating
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing de-icing systems for UAV propellers are unsuitable due to their weight and complexity, and current heating methods provide uniform heating limited to specific parts of the propeller, failing to address ice formation across the entire blade surface.
Innovation Solution
A propeller blade design incorporating a resistive wire along the leading edge connected to a conductive glue and carbon fiber fabric, forming a complete electrical circuit that allows for non-uniform heating across the entire blade surface, using the carbon fiber fabric to return current and provide heat where needed.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If mechanical or chemical de-icing systems are used on large aircraft, then ice formation is prevented, but significant weight is added to the aircraft
Solution Approach 1:
The patent extracts the de-icing function from heavy mechanical/chemical systems and implements it through a lightweight resistive heating wire embedded in the propeller blade. This extraction allows ice prevention without the weight penalty of traditional systems, specifically targeting the propeller blade where ice formation is most critical.
Solution Approach 2:
The patent replaces mechanical/chemical de-icing systems with an electrical heating system. Instead of using mechanical removal or chemical coatings, the invention uses electrical resistance heating to melt ice, thereby eliminating the need for heavy mechanical components or chemical substances.
2Reliability
If heating wire or heating pad-based electro-thermal de-icing techniques are used, then ice formation is prevented, but uniform heating is limited to specific parts of the propeller
Solution Approach 1:
The patent applies local quality by concentrating the heating effect at the leading edge of the propeller blade where ice formation is most prevalent, while the carbon fiber fabric provides distributed heating across the entire blade surface. This targeted approach ensures effective ice prevention where needed most without wasting energy on areas less susceptible to icing.
Solution Approach 2:
The patent uses a composite de-icing system combining a resistive heating wire embedded in the leading edge with the carbon fiber fabric structure of the blade itself. This composite approach allows the heating function to be integrated into the existing blade structure, providing both localized and distributed heating capabilities.
3Reliability
If a complete non-uniform heating system is implemented across the entire blade surface, then ice formation is prevented throughout, but system complexity increases
Solution Approach 1:
The patent makes the carbon fiber fabric serve multiple functions: it provides the structural skin of the propeller blade and simultaneously acts as a conductive heating element when electrical current flows through it. This multi-functionality eliminates the need for separate heating components, thereby reducing overall system complexity while achieving comprehensive heating coverage.
Solution Approach 2:
The patent merges the structural carbon fiber fabric with the heating function by embedding a resistive wire in the leading edge and using the carbon fiber fabric as both the blade skin and the return path for electrical current. This merging of functions integrates the heating system into the existing blade structure without adding separate complex components.
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
This design effectively prevents ice formation on the entire propeller surface by concentrating heat where it is most needed, reducing power consumption and maintaining aerodynamic properties without adding weight or complexity.
Implementation Method 1
a resistive wire extending along the leading edge of the blade body from the hub end to the conductive glue; wherein the resistive wire, the conductive glue and the carbon fiber fabric provide a conductive path for an electrical current in an electrical circuit
Implementation Method 2
the resistive wire, the conductive glue and the carbon fiber fabric provide a conductive path for an electrical current in an electrical circuit from the hub end through the resistive wire to the conductive glue, and then from the conductive glue to the carbon fiber fabric in the skin of the blade body
Data Source
AI summary
A propeller blade comprising a de-icing system is described, wherein the propeller blade comprises a blade body 1 comprising a carbon fiber fabric skin, a leading edge 11, a trailing edge 12, a hub end 9 and a tip end 10. The blade body 1 comprises a resistive wire 4 that extends along the leading edge 11 to a conductive glue 6. The resistive wire 11, the conductive glue 6 and the carbon fiber fabric in the skin of the blade body 1 form a conductive path for an electrical current. A propeller comprising a plurality of the propeller blades, a UAV comprising one or more of the propellers are also described.