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High-pressure air resource consumption calculation method for large-scale icing wind tunnel

A high-pressure air and resource consumption technology, applied in the field of wind tunnel testing, can solve the problem of not being able to identify different air supply methods, and achieve the effect of accurate calculation results

Active Publication Date: 2020-12-11
CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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Problems solved by technology

[0005] The purpose of the present invention is to provide a calculation method for high-pressure air resource consumption in a large-scale icing wind tunnel, aiming to solve the technical problem that the calculation method in the prior art cannot identify different air supply methods

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  • High-pressure air resource consumption calculation method for large-scale icing wind tunnel

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[0036] Aspects of the invention will be described more fully hereinafter with reference to the accompanying drawings. This invention may, however, be embodied in many different forms and should not be construed as limited to any specific structure or function presented throughout this invention. Rather, these aspects are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. Based on the teachings herein one skilled in the art will appreciate that the scope of the invention is intended to encompass any aspect disclosed herein, whether implemented alone or in combination with any other aspect of the invention. For example, it may be implemented using any number of means or implementations presented herein. Additionally, in addition to the aspects of the invention presented herein, the scope of the invention is intended to encompass an apparatus or method implemented using other structures, f...

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Abstract

The invention is applicable to the technical field of wind tunnel tests, and provides a high-pressure air resource consumption calculation method for a large-scale icing wind tunnel. The method comprises the following steps: constructing a topological structure model; establishing a monitoring system; acquiring the state of a large icing wind tunnel and the state of a high-pressure air system; acquiring field pressure consumed by the large icing wind tunnel; judging the air supply mode of the large icing wind tunnel; updating the topological structure model to obtain the pipeline volume V of the large icing wind tunnel; and calculating the high-pressure air resource consumption of the large icing wind tunnel through a differential pressure method. According to the method, the actual physical topological structure relationship between the high-pressure air system and the large-scale icing wind tunnel is expressed in a mode of constructing the model, so the air supply mode of the large-scale icing wind tunnel can be judged, and the high-pressure air resource consumption can be calculated according to different air supply modes.

Description

technical field [0001] The invention belongs to the technical field of wind tunnel tests, in particular to a method for calculating high-pressure air resource consumption in a large icing wind tunnel. Background technique [0002] The large-scale icing wind tunnel is a ground test equipment for studying the icing form, icing tolerance and anti-icing technology of the windward surface of different components and the external sensor part of the detection instrument when aircraft such as aircraft fly under icing weather conditions. Among them, the spray system is the core supporting equipment of the large-scale icing wind tunnel. The high-pressure air resource is used as the driving gas, and the spray medium is sprayed after impacting the spray medium in the mixing chamber inside the nozzle through the high-pressure air flow, so as to obtain the aircraft passing through the supercooled water droplets Simulated cloud and fog environment when flying through clouds. [0003] Larg...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/18G06F16/23
CPCG06F17/18G06F16/23Y02A90/10
Inventor 王小飞罗昌俊马永一司洞洞郑娟黄智强明丽洪
Owner CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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