Process layout method for conventional hypersonic speed wind tunnel

Abstract

The invention discloses a process layout method for a conventional hypersonic speed wind tunnel. The process layout method includes the steps that a fixed supporting base for bearing axial force of components before a test section of the conventional hypersonic speed wind tunnel is arranged on a heat pipeline before a front chamber, the test section is fixed immovably, and axial force generated by an ultra-expanding section in the bearing test of the fixed supporting base is set; the front chamber can move toward the side of the axis of the conventional hypersonic speed wind tunnel to provide space for replacing a spray pipe; two branches are arranged behind the ultra-expanding section, one branch is provided with an ejector, and the other branch is led to a vacuum container, and the two branches are each provided with a valve used for switching and selecting the branches. Due to the technical scheme, the conventional hypersonic speed wind tunnel can have two operation modes, and the capacity for simulating the flight height of an air vehicle of the conventional hypersonic speed wind tunnel is greatly improved.

Description

technical field [0001] The invention belongs to the field of aerodynamics, in particular to a conventional hypersonic wind tunnel process layout method. Background technique [0002] A hypersonic wind tunnel refers to a wind tunnel with a Mach number range of 5 to 12 for the test air flow, which is used to reproduce the flight environment of a hypersonic aircraft. In this environment, the simulation test of the aircraft model is carried out, and relevant parameters are measured. From these tests Parameters get the aerodynamic parameters of the aircraft during flight. Conventional hypersonic wind tunnels usually use resistance or thermal storage heaters to increase the total temperature of the test airflow. Because the wind tunnel needs to consume a lot of power during operation, the hypersonic wind tunnel is mostly a temporary structure. The change of Mach number is mainly obtained by replacing different nozzles. The test section is a closed free jet type. In order to meet ...

AI Technical Summary

Problems solved by technology

The simulation capability of the flight height of the aircraft that can be realized by this layout method is limited. Since the test section needs to move back and forth, the structural complexity of the test section is increased, and the super-expansion section after the test section needs to be equipped with a telescopic structure to meet the test section. Move forward and backward , which makes the structure of the super-expansion section complex and requires higher dynamic sealing

When the wind tunnel adopts a blow-suction layout, the above method is difficult to meet the higher vacuum requirements, thus limiting the ability of the wind tunnel to simulate the flight height of the aircraft

The existing wind tunnel layout method can meet the requirements for small-diameter wind tunnels and wind tunnels with low simulated height requirements, but when the outlet diameter of the wind tunnel nozzle is greater than 1m, the cross-sectional size of the test section reaches the order of 3m×3m. The structural weight reaches 50 tons, and it is difficult to realize its movement and positioning, especially when the simulated height reaches 50-60km, the vacuum degree of the cave body must reach 1Pa, and the leakage rate is not greater than 10 -4 Pa·L / s, moving parts such as expansion joints are difficult to meet the required vacuum degree and leak rate requirements

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