Aircraft Erosion Shield Shock Pulse De-icing
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Solution Overview
Problem
Current de-icing systems for aircraft surfaces, such as thermal, chemical, and mechanical methods, face inefficiencies in removing ice, particularly in terms of energy consumption and aerodynamic performance, especially when dealing with low ice thicknesses and the need for continuous operation to prevent ice accumulation.
Innovation Solution
A pneumatic de-icing system that creates a shock pulse by rapidly delivering and removing pressurized fluid from recesses between the aircraft surface and an erosion shield, using hydraulic or pneumatic activation to deform the shield and expel ice, with the process occurring in less than 25 milliseconds, allowing for efficient ice removal without continuous operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If thermal heating systems are used to remove ice, then ice can be melted and removed, but energy consumption increases significantly
Solution Approach 1:
The patent replaces thermal heating systems with a mechanical shock wave generation system. Piezoelectric actuators generate mechanical shock waves that propagate through the aircraft structure to fracture and remove ice, eliminating the need for continuous thermal heating and significantly reducing energy consumption.
Solution Approach 2:
The system uses periodic pulsed activation of piezoelectric actuators rather than continuous operation. Short bursts of shock waves are generated at intervals to remove ice accumulation, reducing overall energy consumption compared to continuous thermal heating while maintaining effective ice removal.
2Reliability
If mechanical de-icers deform the surface continuously to remove ice, then ice can be removed, but aerodynamic performance deteriorates
Solution Approach 1:
The shock wave system operates in periodic pulses rather than continuous deformation. The brief duration of each shock wave pulse minimizes disruption to the aircraft's aerodynamic surface, allowing the structure to return to its optimal aerodynamic configuration between pulses.
Solution Approach 2:
The system uses high-frequency shock waves that propagate through the structure and fracture ice without causing sustained surface deformation. The vibrational nature of the shock waves allows for effective ice removal while maintaining surface stability and aerodynamic performance.
3Reliability
If pneumatic boots are inflated for several seconds to deform the surface, then ice can be cracked and removed, but the process is slow and energy-intensive
Solution Approach 1:
The patent uses high-frequency shock waves generated by piezoelectric actuators that fracture ice almost instantaneously. This vibrational approach eliminates the several-second inflation time required by pneumatic boots, reducing the de-icing cycle time dramatically.
Solution Approach 2:
The system replaces the slow pneumatic inflation process with rapid shock wave generation. The shock waves propagate through the structure at the speed of sound, fracturing ice in milliseconds rather than seconds, significantly reducing the de-icing cycle time.
4Stability of the object's composition
If thermal systems operate continuously to prevent ice accumulation, then high aircraft performance is maintained, but power consumption increases
Solution Approach 1:
The shock wave system operates periodically rather than continuously. Ice is removed in brief pulses at intervals, allowing the aircraft to maintain optimal performance between cycles while consuming far less power than continuous thermal anti-icing systems.
Solution Approach 2:
The system allows ice to accumulate to acceptable levels and then removes it periodically, rather than requiring continuous active protection. This self-service approach conserves power by operating only when necessary, maintaining surface performance while reducing power consumption.
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 removes ice with minimal impact on aerodynamic performance and low power consumption, suitable for low ice thicknesses, and is durable with fewer components to maintain, enhancing reliability and reducing weight.
Implementation Method 1
The systems create a shock, particularly using hydraulic or pneumatic activation to create a shock pulse. The shock pulse can create a positive deformation of an erosion shield positioned over a recess in the aircraft surface.
Implementation Method 2
The shock pulse is designed to deform the surface of an erosion shield and expulses ice that may have accumulated thereon. The erosion shield covering the recess creates a waved pulse upon application of pressurized fluid to the recess.
Implementation Method 3
A pneumatic de-icing system that creates a shock pulse by rapidly delivering and removing pressurized fluid from recesses between the aircraft surface and an erosion shield
Implementation Method 4
The shock pulse can be created by alternating between delivery of a pressurized fluid and a vacuum
Data Source
AI summary
Systems and methods for de-icing an aircraft surface. The systems create a shock pulse to create a shock activation. The shock pressure is designed to deform the surface of an erosion shield on the surface in order to expulse ice from the wing. The deformation may be between a negative to a positive shape. In one example, the de-icing occurs from a pulse delivered by pressurized fluid injected into and quickly removed from a recess between the aircraft surface and an erosion shield. A pulse of pressurized air or fluid may be injected into one or more cells formed in the recess, together or alternatively, according to the designed effect on the erosion shield surface.