Thermodynamic Loop Heating for Avionic Probes to Simplify Production
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Solution Overview
Problem
Current methods for heating aerodynamic probes on aircraft, such as those using electrical resistances or heat pipes, are complex and costly, and do not effectively prevent ice formation which can obstruct pressure orifices and disrupt measurements.
Innovation Solution
A thermodynamic loop with a closed circuit of heat transfer fluid, including an evaporator and condenser, is used to heat aerodynamic equipment, where the fluid circulates through tubular channels with an empty section, facilitating efficient heat transfer and ice prevention without the need for porous materials or complex assembly processes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If electrical resistances are used to heat the probe, then heating function is achieved, but the production becomes complex and costly
Solution Approach 1:
The heating function is extracted from the probe body itself and relocated to a separate heat source inside the aircraft. The probe receives heat through a thermodynamic loop with heat transfer fluid circulating through tubular tabs, separating the heating mechanism from the probe structure to simplify production.
Solution Approach 2:
A heat transfer fluid acts as an intermediary between the heat source inside the aircraft and the probe exterior. The fluid circulates through a closed thermodynamic loop, transferring thermal energy without direct contact between the heat source and the probe, enabling simplified heating while maintaining functional effectiveness.
2Temperature
If heat pipe with porous material is used to heat the probe, then heating function is achieved, but the production becomes complex due to difficulty of inserting porous material
Solution Approach 1:
The complex porous material structure is completely removed from the solution. Instead of using heat pipes with porous wicking material, the invention uses a simple tubular channel system where heat transfer fluid circulates, eliminating the manufacturing difficulty of inserting and securing porous materials.
Solution Approach 2:
The invention employs a hydraulic system with heat transfer fluid circulating through tubular channels to achieve heat transfer. This fluid-based thermal transport system replaces the solid porous material approach, leveraging fluid dynamics for heat distribution while simplifying manufacturing.
3Temperature
If heating wire is wound around the probe body, then heating function is achieved, but the assembly process becomes complex and costly
Solution Approach 1:
The heating function is extracted from the probe assembly process entirely. Instead of winding heating wires around the probe during manufacturing, the heating system is separated into an independent thermodynamic loop with fluid circulation, eliminating the complex wire-winding and brazing operations.
Solution Approach 2:
The mechanical heating wire system is replaced with a thermodynamic fluid circulation system. Heat transfer occurs through thermal conduction from the fluid to the probe walls, substituting the mechanical wire-winding process with a fluid-based thermal field approach that simplifies assembly.
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 solution simplifies the production and operation of heated aerodynamic probes, reduces pressure losses, and ensures effective ice prevention, maintaining accurate airflow measurements by maintaining consistent and homogeneous temperatures across the equipment.
Implementation Method 1
Currently, in most cases, heating is done using electrical resistances embedded in the appendages. The heating is done by Joule effect.
Implementation Method 2
a thermodynamic loop comprising a closed circuit in which a heat transfer fluid circulates, the closed circuit comprising an evaporator associated with means forming a heat source arranged inside the aircraft and a zone in which a condensation of the heat transfer fluid can occur
Implementation Method 3
a thermodynamic loop comprising a closed circuit in which a heat transfer fluid circulates, the closed circuit comprising an evaporator associated with means forming a heat source arranged inside the aircraft and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it
Data Source
AI summary
The invention relates to an aircraft provided with at least one piece of aeronautic equipment fastened to the outside skin of the aircraft and a heater for heating the piece of aeronautic equipment. The heater is in the form of a thermodynamic closed circuit loop circulating heat-transfer fluid and including an evaporator and a heat source located inside the aircraft and a condenser located in the piece of aeronautic equipment or an appendage thereto. Fasteners in the form of tubular tabs include tubular channels for circulating the heat-transfer fluid.