Aspirating type propulsion test simulation method based on high-temperature pulse wind tunnel

Abstract

The invention discloses an aspirating type propulsion test simulation method based on a high-temperature pulse wind tunnel. The aspirating type propulsion test simulation method based on the high-temperature pulse wind tunnel comprises the following steps that (1) an aspirating type propulsion test system is established; (2) an A group cold test is conducted, and test data of non-fuel spouting columns and air incoming flow are measured; (3) a B group cold test is conducted, and the test data of the non-fuel spouting columns and the air incoming flow are measured; (4) a C group cold jet test isconducted, and cold jet test data flown from flue spouting and nitrogen flow are measured; (5) the differences of A, B, and C test data are compared, sprouting influence, burning characteristic and colt and hot performance analyses are completed, and stimulation on aspirating type propulsion is realized. According to the aspirating type propulsion test simulation method based on the high-temperature pulse wind tunnel, through sprouting control of fuel and replacement of test gas, three groups of control test stimulation methods A, B and C are formed, the burning characteristic of the aspirating type propulsion test can be judged, performance incremental test data of cold and hot performances can be obtained, and the aspirating type propulsion test simulation method can further be used forthe fuel sprout disturbance characteristic analysis of the aspirating type propulsion test.

Description

technical field [0001] The invention relates to an air-breathing propulsion test simulation method, which belongs to the technical field of high-temperature hypersonic pulse wind tunnel tests. Background technique [0002] The fusion of scramjet and other power such as rocket or turbine engine to form combined cycle power can realize the flight of aircraft across airspace, wide speed range and high maneuverability. It is an important research hotspot in the field of hypersonics at home and abroad. As the only air-breathing propulsion device capable of achieving hypersonic flight, the scramjet has a wide range of Mach numbers. Theory shows that the Mach number spans from 5 to 25. Matching ground test equipment and test simulation methods are required to carry out relevant experimental research . However, limited by heating capacity, currently only high-temperature pulse wind tunnels such as high-enthalpy shock tunnels and expansion wind tunnels (such as T4 and X3 in Australi...

AI Technical Summary

Problems solved by technology

For high-temperature pulsed wind tunnels with a test time of only a few milliseconds, this test simulation method is completely inapplicable

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