2-m-Maglitude free-piston-driven high-enthalpy shock tunnel

Abstract

A 2-m-maglitude free-piston-driven high-enthalpy shock tunnel comprises a high-pressure gas storage chamber, a piston launching mechanism, a piston, a compression tube, a piston stop mechanism, a maincapsule mechanism, a shock wave tube, a small capsule mechanism, a spray tube, a test segment, a track and a support system. The high-pressure gas storage chamber is arranged at the upstream of the piston launching mechanism and stores high-pressure air. After being launched through the piston launching mechanism, the piston may move to the downstream of the compression tube at increased speed; when the piston arrives at the tail end of the compression tube, most energy is transmitted to helium-argon mixed light gas, and high-temperature high-pressure gas is generated; at this moment, a membrane of the main capsule mechanism breaks, incoming shock wave is generated and passes through the shove wave tube until its tail end, the shoe wave may be reflected, and high-temperature high-pressuregas is generated to cause breakage of a membrane of the small capsule mechanism. The high-temperature high-pressure test gas passes through the spray pipe to the test segment, and free stream conditions required are acquired.

Description

technical field [0001] The invention relates to a high-enthalpy shock wind tunnel driven by a 2m-level free piston, which can not only study aerodynamic basic research such as ultra-high-speed high-temperature real gas effects, but also carry out engineering applications such as scramjet engines and space re-entry vehicles. Research. Background technique [0002] The wide range of flight conditions of hypersonic vehicles and the unique physical phenomena that need to be studied make a single hypersonic test equipment unable to meet the test requirements, resulting in the diversification of hypersonic test equipment. For wind tunnel tests, it is currently impossible to carry out a series of experimental studies such as aerothermodynamics, aero-optics, and aeroacoustics within the entire flight envelope, and can only evaluate the "critical path" before the flight test. In the low hypersonic region with a Mach number of 5-12, the simulation of the ideal gas flow Mach number an...

AI Technical Summary

Problems solved by technology

The high-temperature effect brought about by ultra-high-speed flow cannot be reproduced in conventional "cold" state hypersonic ground equipment

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