Method for controlling adjusting dynamic pressure flow field for large direct-current blow-down supersonic wind tunnel

A control method, temporary flushing technology, applied in the direction of electric fluid pressure control, etc., can solve the problems of uncontrollable total pressure rise rate, inability to control multiple total pressure steps, and inability to reduce speed pressure, etc., to achieve control parameters It is convenient to set, meet the requirements of flutter test, and the effect of high precision of total pressure control

Active Publication Date: 2017-03-22
INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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AI Technical Summary

Problems solved by technology

This conventional control method mainly has the following defects: 1. Multiple total pressure steps cannot be controlled in a single test; 2. The rising rate of the total pressure is uncontrollable
3. The speed pressure cannot be reduced when the car is turned off
The Mach number of the supersonic win...

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  • Method for controlling adjusting dynamic pressure flow field for large direct-current blow-down supersonic wind tunnel
  • Method for controlling adjusting dynamic pressure flow field for large direct-current blow-down supersonic wind tunnel
  • Method for controlling adjusting dynamic pressure flow field for large direct-current blow-down supersonic wind tunnel

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Embodiment Construction

[0032] All features disclosed in this specification, or steps in all methods or processes disclosed, may be combined in any manner, except for mutually exclusive features and / or steps.

[0033] In the supersonic wind tunnel, the nozzle profile and the super-expansion section profile are adjusted to the corresponding positions according to the Mach number requirements before the test. During the test, the total pressure in the stable section is adjusted to obtain the supersonic flow field under the corresponding Mach number conditions. The main pressure regulating valve control system is responsible for controlling the total pressure in the stable section; the injection pressure regulating valve control system is responsible for controlling the injection pressure; the model insertion mechanism control system is responsible for controlling the insertion and withdrawal of the model.

[0034] The supersonic wind tunnel speed pressure calculation formula is as follows:

[0035] q=0...

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Abstract

The invention, which relates to the field of supersonic wind tunnel test control, discloses a method for controlling an adjusting dynamic pressure flow field for a large direct-current blow-down supersonic wind tunnel. With the method provided by the invention, a problem that the supersonic flutter testing requirement can not be met because multi-step total pressure control can not be realized at single flight and the total pressure rising rate can not be controlled according to the conventional supersonic wind tunnel control method can be solved. The method comprises: wind tunnel starting and pressurizing are carried out and a flow field s established; a total pressure is adjusted stably; an adjusting dynamic pressure is adjusted; and flying machine closing is carried out by the wind tunnel. And different closing strategies are employed based on different situations, so that flying machine closing is realized securely by the wind tunnel. With the method, the requirement on adjusting dynamic pressure flow field control of the supersonic wind tunnel by a flutter test is met. The method has advantages of reliable operation, convenient parameter giving, low total pressure control overshooting, and high precision.

Description

technical field [0001] The invention relates to the field of supersonic wind tunnel test control in the aerospace industry, in particular to a variable-speed pressure-flow field control method suitable for direct-current impulse supersonic wind tunnels. Background technique [0002] Flutter is a destructive structural vibration that occurs when the flight pressure exceeds a critical value during the flight of aircraft, missiles and other aircraft. It is a self-excited vibration under the interaction of aerodynamic force, elastic force and inertial force. Due to the harmfulness of flutter, flutter is absolutely not allowed within the flight envelope of the aircraft. The purpose of the aircraft flutter test is to reproduce the flutter phenomenon with a dynamic similar model in the wind tunnel, understand the flutter characteristics of the aircraft, determine the flutter critical speed pressure and flutter frequency under dangerous flight conditions, and provide a flight envelo...

Claims

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Application Information

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IPC IPC(8): G05D16/20
CPCG05D16/20
Inventor 周波张林杨洋余立涂清高川林学东闫煜吕彬彬苏北辰邓吉龙蒋鸿郁文山
Owner INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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