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Cyclic flexing environmental chamber and method

A technique of chambers, devices, applied in the field of determining the operational properties of material systems, which can solve problems such as reduced motor/actuator functionality

Pending Publication Date: 2020-06-26
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In addition, the functionality of the motor / actuator is also reduced during high temperature operation (e.g. 70°C or higher)

Method used

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  • Cyclic flexing environmental chamber and method
  • Cyclic flexing environmental chamber and method
  • Cyclic flexing environmental chamber and method

Examples

Experimental program
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example

[0148] Material

[0149] Gamry Reference 600 Potentiostat (2)

[0150] Thermotron Se-2000 Environmental Chamber with Integrated Flexure Device

[0151] Omega wireless temperature / humidity sensor or Ethernet data connection

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PUM

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Abstract

The present invention relates to a cyclic flexing environmental chamber and a method. At one aspect, an apparatus includes a chamber configured to control one or more of humidity, pressure, and temperature and a caliper configured to flex a material system. The chamber includes a housing disposed within the chamber and having an insulating material, and a motor or actuator disposed within the housing. The chamber includes an inlet tube coupled with the housing at a first end and coupled with a first wall of the chamber at a second end. In one aspect, a method for determining material properties includes exposing the material system to a relative humidity of from 0% to 98% in the chamber, and flexing the material system at a first temperature. The chamber includes the housing disposed within the chamber and the motor disposed within the housing, and the method includes operating the motor at a second temperature different from the first temperature during flexing.

Description

technical field [0001] Aspects of the disclosure relate generally to methods for determining operational performance of a material system. Background technique [0002] During its operational life, an aircraft will experience repeated and severe conditions, which may cause some of the aircraft's components to deteriorate. This degradation may take the form of, for example, coating failure and / or corrosion. Corrosion can reduce the integrity and strength of aircraft components. More specifically, material systems such as aircraft components include fuselage or skin panels, coated lap joints between two metal panels, or wing-to-fuselage assemblies on the exterior of an aircraft. During the service of an aircraft, material systems may corrode over time due to exposure to mechanical and chemical stress. Before determining a material's suitability for use as an aircraft material system, it may be desirable to determine the corrosion propensity of the material system. However,...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M5/00G01N17/00
CPCG01M5/0083G01N17/00G01N17/002G01N3/32G01N3/18G01N3/20G01N2203/022G01N2203/0242G01N2203/0224G01N2203/0476G01N2203/023G01N2203/024G01N17/02G01N17/006
Inventor 克里斯滕·史密斯·威廉姆斯布鲁诺·萨莫拉诺·森德罗斯戴维·阿达姆·杰克逊
Owner THE BOEING CO