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Protection system for anti/de-icing experiment of refrigeration tunnel

A protection system and prevention technology, applied in the field of protection systems, can solve the problems of affecting the air duct flow field, reducing the accuracy of the experiment, and the large size of the protective cover. Effect

Active Publication Date: 2019-04-26
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] At present, large-scale icing wind tunnels in China use built-in protective devices to protect the test pieces. The protective cover has a large structure and is only used in large-scale wind tunnels. The built-in protective structure will affect the flow field in the air duct and reduce the accuracy of the experiment.

Method used

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  • Protection system for anti/de-icing experiment of refrigeration tunnel
  • Protection system for anti/de-icing experiment of refrigeration tunnel
  • Protection system for anti/de-icing experiment of refrigeration tunnel

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Embodiment Construction

[0025] see figure 1 As shown, the present invention discloses a protective system for anti-icing and deicing experiments in an icing wind tunnel, including an air duct 4 , a protective cover 3 , an electric heating unit, and an air slide 1 located outside the air duct 4 . The air duct 4 is the experimental space for the aircraft wing icing experiment, and the simulated wing 5 to be tested is placed in the air duct 4 in advance, and the air in the air duct carries supercooled water droplets to impact. However, before the expected supercooled water droplet state is formed, it will take a period of time for the subcooled water droplets that do not reach the standard to be ejected from the air duct until the supercooled water droplet standard is reached, and the supercooled water droplets that do not reach the standard cannot contact the simulated wing 5 . At this time, the protective cover 3 needs to be used to protect the simulated wing 5 . Such as figure 1 As shown, the cros...

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Abstract

The invention discloses a protection system for an anti / de-icing experiment of a refrigeration tunnel. The protection system comprises an air duct, a protective cover, an electric heating unit and a pneumatic sliding table positioned outside the air duct, wherein the cross section of the protective cover is arc-shaped; an arc-shaped slot matched with the shape of the protective cover is formed inthe air duct; and the pneumatic sliding table is connected to one end of the protective cover and drives the protective cover to be inserted into the arc-shaped slot or extracted from the arc-shaped slot. The protection system is used for protecting the tested simulated aircraft wings in experiments. The protection system disclosed by the invention has the advantages of being simple and convenientto operate, simple in structure, convenient to mount, low in energy consumption, convenient to maintain, obvious in effect and the like, and the anti / de-icing experiment quality of the refrigerationtunnel can be effectively improved.

Description

technical field [0001] The invention relates to the field of aircraft anti-icing tests, in particular to a protection system for anti-icing tests in an icing wind tunnel. Background technique [0002] Aircraft icing has always been one of the main threats to aviation safety. In order to study aircraft anti-icing, a ground icing wind tunnel was established. Ground anti-icing experiments have higher requirements on the freezing environment, mainly including wind speed in the air duct, freezing temperature, liquid water content (LWC), and average particle size (MVD). At the beginning of the experiment, the spray rack sprayed water, and the liquid water hit the surface of the test piece after being supercooled. Due to the freezing temperature, liquid water content and average particle size, it took a period of time to reach a stable state after the spray rack was opened. The liquid water hitting the surface of the test piece before the experimental state is stable does not meet...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 朱春玲王渊朱程香赵宁苗波陶明杰田甜
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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