Pressure measuring device and pressure measuring method

A pressure measurement device and pressure measurement technology, applied in the field of wind tunnel testing, can solve problems such as pressure measurement over-range

Active Publication Date: 2021-02-05
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0006] The purpose of the present invention is to provide a pressure measuring device and a pressure measuring method, aiming at solving the technical problem of over-range in the pressure measuring in the prior art

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  • Pressure measuring device and pressure measuring method
  • Pressure measuring device and pressure measuring method
  • Pressure measuring device and pressure measuring method

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Embodiment Construction

[0042] 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 suitable for the technical field of wind tunnel tests, and provides a pressure measuring device and a pressure measuring method. The pressure measuring method comprises the followingsteps that: a pressure measuring end in the pressure measuring device is connected with each measuring point of a test model located in an icing wind tunnel; when the icing wind tunnel is in a staticstate, a pressure adjuster is adjusted to enable the adjusted pressure in a variable-pressure cavity, the adjusted pressure in a constant-pressure cavity and the internal pressure of the icing wind tunnel in the static state to be equal; when the icing wind tunnel is in a windward state, the reading of a differential pressure scanning valve is enabled to be positioned on the two sides of the measuring range of the differential pressure scanning valve; when the wind speed in the icing wind tunnel is stable, the attack angle of a test model is changed, and the reading of the differential pressure scanning valve is enabled to be located on the two sides of the measuring range of the differential pressure scanning valve; and the pressure of each measuring point is calculated. According to thepressure measuring device and the pressure measuring method provided by the invention, the differential pressure scanning valve cannot be over-range, and the safety of measurement is ensured.

Description

technical field [0001] The invention belongs to the technical field of wind tunnel tests, and in particular relates to a pressure measuring device and a pressure measuring method. Background technique [0002] Icing is one of the problems that are always concerned during flight. Icing will damage the aerodynamic shape of the windward model of the aircraft and affect the flight performance. Therefore, it is very meaningful to study the icing of aircraft models in different meteorological environments, to ensure flight safety and to promote anti-icing means. [0003] At present, research on aircraft icing mainly relies on conditional tests carried out in mature special icing wind tunnels. The icing wind tunnel creates an environment that simulates real flight icing for the test, but icing is also affected by flight attitude. constraint, exactly the angle of attack of the aircraft. [0004] Therefore, for the two variables of the icing wind tunnel and the aircraft model, expe...

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Application Information

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IPC IPC(8): G01M9/06
CPCG01M9/06
Inventor 冉林熊建军易贤赵照张鸿健李自雨张轲
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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