Variable Stiffness Shield for Aircraft Ice De-bonding
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Solution Overview
Problem
Aircraft components, such as wings, are prone to ice accretion during flight, which affects performance and safety, and existing de-icing systems may not efficiently de-bond ice due to reliance on uniform stress distribution and high energy consumption.
Innovation Solution
An electro-mechanical de-icing system featuring a shield with variable stiffness across its width and length, designed to deform in a twist-like manner, generating uniform shear stresses to break ice cohesion forces, with actuators positioned between the shield and the wing to apply forces that de-bond ice without requiring high energy.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If uniform stress distribution is used in existing de-icing systems, then the system structure is simple, but the de-bonding efficiency is low and high energy is consumed
Solution Approach 1:
The shield is designed with non-uniform stiffness distribution, where the stiffness varies across the width of the shield. This local variation in stiffness creates twist-like deformation patterns when force is applied, generating uniform shear stresses that effectively target ice cohesion forces for de-bonding, thereby improving efficiency while reducing overall energy requirements
Solution Approach 2:
The shield employs asymmetric stiffness distribution rather than uniform symmetry. By making the stiffness non-uniform across the width, the system creates optimized deformation patterns that generate effective shear stresses for ice de-bonding, achieving better performance with lower energy consumption compared to symmetric uniform designs
2Reliability
If high force is applied to break ice cohesion, then ice de-bonding is effective, but energy consumption increases and actuator size increases
Solution Approach 1:
The system changes the mechanical parameters of the shield by varying its stiffness distribution. This parameter change allows the shield to deform in a twist-like manner under reduced force conditions, generating sufficient shear stresses to break ice cohesion without requiring large actuators or excessive energy input
3Ease of manufacture
If uniform stiffness shield is used, then manufacturing is simpler, but de-icing performance is reduced
Solution Approach 1:
The shield incorporates local variations in stiffness through features such as stiffeners and varying thickness distributions. These localized modifications create the necessary twist-like deformation patterns during actuation, significantly improving de-icing performance while maintaining reasonable manufacturing feasibility through standard structural reinforcement techniques
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 system effectively de-bonds ice with reduced energy requirements, allowing for smaller actuators and control units, decreased power consumption, and improved de-icing performance independent of ice thickness, while maintaining structural integrity.
Implementation Method 1
generating uniform shear stresses to break ice cohesion forces
Implementation Method 2
the shield has a variable (non-uniform) stiffness across its width such that its deformation may be twist-like when the shield is subjected to a force
Implementation Method 3
with actuators positioned between the shield and the wing to apply forces that de-bond ice
Data Source
Figure 1~2
Figure 3A~3B
Figure 4
AI summary
An de-icing system comprising a shield that is configured to deform in a pre-determined way that de-bonds accreted ice. In some embodiments, the shield has a variable (non-uniform) stiffness across its width and/or length such that it undergoes a twist-like or other suitable deformation when subjected to a force. In some embodiments, the system includes a plurality of electro- mechanical actuators configured to generate the force applied to the shield.