A control method of variable velocity pressure flow field in a large direct current impulse supersonic wind tunnel
A control method and a rush-type technology, applied in the direction of electric fluid pressure control, etc., can solve the problems of inability to carry out multiple total pressure step control, inability to reduce rapid pressure, uncontrollable total pressure rise rate, etc., to meet the requirements of vibration. The effects of vibration test requirements, high total pressure control accuracy, and convenient control parameters are given.
Active Publication Date: 2020-01-14
INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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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 wind tunnel is determined by the preset nozzle profile before the test, and the total pressure is controlled by the main pressure regulating valve in the test. Therefore, the control method of the variable velocity pressure flow field in the transonic wind tunnel is not suitable for the supersonic wind tunnel
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[0032] All the features disclosed in this specification, or all disclosed methods or steps in the process, except for mutually exclusive features and / or steps, can be combined in any manner.
[0033] In the supersonic wind tunnel, the nozzle profile and the super-expanded section profile are adjusted to the corresponding positions according to the Mach number requirements before the test. During the test, the total pressure of the stable section is adjusted to obtain the supersonic flow field under the corresponding Mach number. The main pressure regulating valve control system is responsible for controlling the total pressure of the stable section; the ejection pressure regulating valve control system is responsible for controlling the ejection pressure; the model insertion mechanism control system is responsible for controlling the insertion and withdrawal of the model.
[0034] The velocity pressure calculation formula of the supersonic wind tunnel is as follows:
[0035] q=0.7×P ...
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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 a direct current impulse type supersonic wind tunnel. Background technique [0002] Flutter is a kind of destructive structural vibration that occurs after the flight speed pressure exceeds a critical value in 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 hazard of flutter, aircraft flutter is absolutely not allowed within the flight envelope. 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...
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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