Thermally Isolated Pneumatic Lines for Air Data Probes
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Solution Overview
Problem
Air data probes for aircraft face challenges in extreme cold conditions where moisture and ice accumulation in pneumatic lines can hinder accurate measurements, despite existing heating solutions being inadequate due to thermal conduction from large aircraft components.
Innovation Solution
The air data probe design incorporates thermally isolated pneumatic lines through isolation bores in the baseplate and faceplate, with a self-regulating heating system within an isolation bracket to maintain the pneumatic lines' temperature, minimizing ice and moisture buildup.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If electrical heating elements are installed in the pneumatic lines, then ice and moisture buildup is reduced, but the heating becomes ineffective in extreme cold conditions due to thermal conduction from large aircraft components
Solution Approach 1:
A thermal isolation bracket made of low thermal conductivity material is introduced as an intermediary between the aircraft skin and the pneumatic line. This bracket contains a heating element and thermally isolates the pneumatic line from the aircraft skin, preventing heat loss to the large thermal mass of the aircraft components while maintaining the effectiveness of the heating element in preventing ice buildup.
Solution Approach 2:
The system is segmented into distinct thermal zones: a heated isolation bracket containing the pneumatic line and heating element, separated from the unheated aircraft skin by low thermal conductivity material. This segmentation prevents thermal conduction losses to the large aircraft components while maintaining localized heating effectiveness.
2Strength
If the aircraft skin and baseplate are thermally connected to the pneumatic lines, then structural support is provided, but ice and moisture accumulation occurs in the pneumatic lines during extreme cold conditions
Solution Approach 1:
The isolation bracket serves as a thermal intermediary that provides structural support for the pneumatic line while simultaneously preventing thermal conduction from the cold aircraft skin to the pneumatic line. This eliminates ice and moisture accumulation while maintaining structural integrity.
Solution Approach 2:
The system applies local thermal isolation specifically at the critical interface where the pneumatic line connects to the aircraft skin. The low thermal conductivity material is placed only where needed to prevent heat loss, while other parts of the system maintain their normal thermal characteristics.
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 effectively prevents ice and moisture accumulation in pneumatic lines by thermally isolating them from the aircraft components, ensuring accurate measurements even in extreme cold conditions, and reduces the risk of complete blockage.
Implementation Method 1
an electrical heating element can be arranged within the interior passage of an air data probe to provide heat sufficient to drive off moisture and ice
Implementation Method 2
The isolation bracket is made of a material having a low thermal conductivity so as to prevent formation of ice and/or moisture within the pneumatic line
Data Source
Figure 1a~1b
Figure 2a~2c
Figure 3a~3b
AI summary
The invention provides a probe (100) for an aircraft (80) including a strut (102) having an interior passage (104) accommodating a plurality of pneumatic lines (106), a probe head (108) extending from the strut and having at least one inlet (110,112) opening communicating with the pneumatic lines, a baseplate (114) situated below the strut for attaching the probe to the aircraft (80), and a manifold (116) situated below the baseplate for communicating with the pneumatic lines, wherein the baseplate is adapted and configured so that the pneumatic lines communicating with the manifold are thermally isolated from the baseplate. The invention also provides a method of thermally isolating at least one pneumatic line in an aircraft probe.