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Practical operation and simulation integrated wind tunnel test process verification method

A technology of wind tunnel test and verification method, applied in the field of wind tunnel test, which can solve problems such as explosion, waste of manpower and material resources, high cost, etc., and achieve the effect of ensuring safety and reducing workload

Active Publication Date: 2021-02-09
中国空气动力研究与发展中心超高速空气动力研究所
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For hypersonic high-temperature wind tunnels, if these risk factors exist, once the actual operation starts, the price paid will be extremely high: ranging from data invalidation and waste of manpower and material resources; to severe incidents such as damage to wind tunnel equipment, explosions, and combustion

Method used

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  • Practical operation and simulation integrated wind tunnel test process verification method

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Embodiment 1

[0040] This embodiment is an application example of a hypersonic high temperature wind tunnel. The specific situation is as follows: the newly revised test procedure requires that the throttle valve be opened when T=0 seconds; the main valve be opened when T=1 second; If the temperature is greater than 60%, it will be transferred to the liquid oxygen filling process, otherwise it will be transferred to the emergency stop operation process. The wind tunnel control program is currently in operation, with the main valve and throttle closed. According to the data given by the valve manufacturer, the full opening time of the throttle valve is 4 seconds, the valve position increases linearly with time, and the opening time of the main valve is 1.85 seconds. The simulation process of the test process includes the following steps:

[0041] a. The operator sets the full throttle valve opening time to 4 seconds and the main valve opening time to 1.85 seconds through the host computer;...

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Abstract

The invention discloses a practical operation and simulation integrated wind tunnel test process verification method. The wind tunnel test process verification method is based on a wind tunnel controlprogram, a corresponding control module is arranged for each field device in the wind tunnel control program, and each control module is provided with a mode switching interface, a set of actual input and output interface, a set of program control intermediate interface and a simulation sub-module. The wind tunnel test process verification method can directly simulate the action of the wind tunnel equipment in the wind tunnel control program, test the time sequence and logic interlocking relationship in the wind tunnel test flow, and safely, effectively and quickly complete the related verification work of the test flow. The wind tunnel test process verification method does not need additional software and hardware resources and can be realized in any general controller and matched development software.

Description

technical field [0001] The method belongs to the technical field of wind tunnel tests, and specifically relates to a wind tunnel test flow verification method integrating practical operation and simulation. Background technique [0002] Hypersonic high-temperature wind tunnel safety issues are prominent. Wind tunnel tests involve various dangerous media such as flammable, explosive, strong oxidation, and cryogenic. The time and economic cost of the wind tunnel test is high: before the wind tunnel test, the inspection and preparation process of nearly 10 systems and hundreds of equipment in the hypersonic high-temperature wind tunnel takes an average of 4 to 8 hours; the hypersonic high-temperature wind tunnel has a caliber of 3 The meter level, the flow rate is hundreds of kilograms per second, and the consumption cost of a dynamic combustion reaches more than 100,000 yuan. The wind tunnel test process is complicated, and it is necessary for the wind tunnel control program ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B17/02G01M9/02G06F30/28G06F113/08G06F119/14
CPCG01M9/02G05B17/02G06F30/28G06F2113/08G06F2119/14
Inventor 马晓宇王南天部绍清唐绍杰曾令国于子泉朱超
Owner 中国空气动力研究与发展中心超高速空气动力研究所