Biphase Heating for Aircraft Aerodynamic Probes
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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 at high altitudes, which can obstruct pressure orifices and disrupt airflow measurements.
Innovation Solution
A thermodynamic loop with a closed circuit using a heat transfer fluid that circulates through a tubular channel with an empty section, allowing for efficient heat transfer and ice prevention, integrated with additive manufacturing for simplified production and flexible installation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If electrical resistances are used to heat aerodynamic probes, then heating function is provided, but production complexity and cost increase
Solution Approach 1:
The patent extracts the heating function from the probe structure itself by using a separate thermodynamic loop system. The heating fluid circulates through channels in the probe mounting structure rather than embedding heating elements within the probe, simplifying probe production while maintaining heating capability.
Solution Approach 2:
The patent combines the heating function with the probe mounting structure (base). The thermodynamic loop integrates the heating circuit into the base structure that already supports the probe, eliminating the need for separate heating components and reducing overall system complexity.
2Temperature
If heat pipes with porous material are used for heating, then heating function is provided, but manufacturing difficulty increases
Solution Approach 1:
The patent removes the complex porous material component from the heating system. Instead of using heat pipes requiring porous wick material, the invention uses a simple thermodynamic loop with fluid circulation through channels, eliminating manufacturing difficulties associated with porous material insertion.
Solution Approach 2:
The patent employs a hydraulic/thermodynamic approach using fluid circulation through channels rather than solid-state heat pipes. The heating fluid (water-glycol mixture) circulates through the base and probe mounting structure, providing efficient heat transfer without requiring porous materials or complex capillary structures.
3Object-affected harmful factors
If heating power is increased to prevent ice formation, then ice prevention is improved, but energy consumption increases
Solution Approach 1:
The patent utilizes phase transition of the heating fluid (water-glycol mixture) to provide efficient heat transfer. The fluid absorbs heat from the aircraft skin and releases it to the probe mounting structure, maintaining temperatures above freezing without requiring excessive heating power.
Solution Approach 2:
The patent uses a composite heating medium (water-glycol mixture) that combines the advantages of water (high specific heat capacity) with glycol (lower freezing point). This composite fluid provides efficient heat transfer while preventing freezing in the circulation system, reducing overall energy 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 solution provides effective heating for aerodynamic probes, preventing ice formation and ensuring accurate airflow measurements while reducing production complexity and costs through the use of a thermodynamic loop and additive manufacturing.
Implementation Method 1
a thermodynamic loop comprising a closed circuit in which a heat transfer fluid circulates, the closed circuit comprising an evaporator and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it
Implementation Method 2
a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it
Implementation Method 3
a thermodynamic loop comprising a closed circuit in which a heat transfer fluid circulates, the closed circuit comprising an evaporator and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it
Data Source
AI summary
A piece of aeronautic equipment intended to equip an aircraft, the equipment piece (25) including at least one part intended to be arranged at a skin (27) outside of the aircraft and heating elements for that part, which include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator and a zone in which condensation of the heat transfer fluid can occur in the appendage to heat it, outside the evaporator, the circuit in which the fluid circulates is formed by a tubular channel with an empty section, at least the part of the piece of equipment arranged outside the aircraft is made by additive manufacturing and includes a fastening base (120) for fastening on the skin of the aircraft from which support elements (130) for a Pitot tube (140) provided with lateral static pressure taps (150) extend.