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Hypersonic aircraft pulsating pressure test sensor optimization arrangement method

A hypersonic, pulsating pressure technology, used in aerodynamic testing, testing of machine/structural components, instruments, etc., can solve the problems of unreasonable sensor arrangement, complicated economic cost pulsating pressure test data, etc., to reduce economic costs, Reduce the effect of damage

Pending Publication Date: 2022-03-29
CHINA ACAD OF AEROSPACE AERODYNAMICS
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Problems solved by technology

[0004] The purpose of the present invention is to provide a hypersonic vehicle pulsation pressure test sensor optimization arrangement method, to solve the problem of unreasonable sensor arrangement of hypersonic pulsation pressure test, to ensure that the pulsation pressure test sensor arrangement in the hypersonic wind tunnel can be realized The purpose of the test can reduce the damage to the aircraft surface caused by installing more sensors, and at the same time reduce the economic cost and the problems of complicated and redundant data of the pulsating pressure test

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Embodiment 1

[0033] Such as figure 1 as shown,

[0034] This embodiment provides a method for optimizing the arrangement of hypersonic vehicle pulsation pressure test sensors, including the following steps:

[0035] Step 1, processing an aircraft model equal in proportion to the pulsation pressure test aircraft model and the same size as the model for the infrared heat map test;

[0036] In this embodiment, the hypersonic wind tunnel test based on infrared heat map technology is to guide the optimal arrangement of high-frequency sensors for pulsation pressure tests. In particular, the principle of infrared heat map technology is to use the principle of thermal radiation to detect the radiation of objects To obtain the temperature of the surface of the model, it is required that the infrared test model material be selected from a specific PEEK material, which has high emissivity, is easy to process, and has stable thermal and physical parameters. Therefore, the present invention adopts th...

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Abstract

The invention provides a hypersonic aircraft pulsating pressure test sensor optimization arrangement method. The method comprises the steps that an aircraft model which is equal to a pulsating pressure test aircraft model in proportion and size is machined; building an infrared thermogram measurement system; the aircraft model is fixed in a hypersonic wind tunnel for an infrared thermogram test, and infrared thermogram data of the windward side and the leeward side of the surface of the aircraft model are collected; heat map data are processed according to infrared heat map image processing software, and heat flow distribution on the surface of the aircraft model is calculated; judging surface flow states of the aircraft model, and determining starting and ending positions of each flow state; and according to the heat flow distribution and the surface flow state, guiding the arrangement of the high-frequency response sensor for the pulsating pressure test of the hypersonic aircraft. According to the invention, the sensor arrangement of the pulsating pressure test carried out in the hypersonic wind tunnel can realize the test purpose and reduce the damage to the profile of the aircraft caused by the installation of a plurality of sensors, and the problems of complicated and redundant pulsating pressure test data are reduced.

Description

technical field [0001] The invention relates to the technical field of hypersonic wind tunnel tests, in particular to a method for optimizing the arrangement of sensors for hypersonic aircraft pulsation pressure tests. Background technique [0002] When a hypersonic vehicle operates in the adjacent space and atmosphere for a long time and at high speed, it is subjected to the comprehensive effects of multiple physical fields such as aerodynamic heat and aerodynamic force. The flow structure of the boundary layer on the outer surface is complex and changeable, especially when the boundary layer is in transition. During this period, the aerodynamic force and aerodynamic heat it receives will change drastically. In order to fully and accurately understand these physical phenomena, the flight environment of atmospheric aircraft is simulated through a wind tunnel on the ground. The hypersonic pulsating pressure is to study and assess the unsteady pulsating pressure characteristic...

Claims

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Application Information

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IPC IPC(8): G01M9/06G01M9/08
CPCG01M9/06G01M9/08
Inventor 李海燕易翔宇林键陈勇富纪锋文帅陈农
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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