Shockwave wind tunnel-based self-starting test device for hypersonic air inlet channel

Abstract

The invention discloses a shockwave wind tunnel-based self-starting test device for a hypersonic air inlet channel. The shockwave wind tunnel-based self-starting test device comprises the hypersonic air inlet channel, a diaphragm, a resistance wire and a delay ignition device, wherein the hypersonic air inlet channel is arranged in a wind tunnel test chamber, an inlet end of the hypersonic air inlet channel is opposite to a wind tunnel nozzle of the wind tunnel test chamber, the diaphragm is mounted at an outlet end of the hypersonic air inlet channel through a diaphragm clamping device, the resistance wire is arranged on the diaphragm, and the delay ignition device is used for conducting the resistance wire so as to ablate the diaphragm according to a preset delay time when a pressure signal is detected from the wind tunnel nozzle. With the adoption of the shockwave wind tunnel-based self-starting test device for the hypersonic air inlet channel, the problem of testing means for the self-starting characteristic study on the hypersonic air inlet channel by using a shockwave wind tunnel is solved, the quasi-steady periodic fluid state of the air inlet channel at a no-start stage can be simulated and is provided with enough duration, the self-starting characteristics of the air inlet channel are viewed within a set time range, and thus, the validity and the repeatability of a self-starting test can be ensured.

Description

technical field [0001] The invention belongs to the technical field of hypersonic speed propulsion, and in particular relates to a self-starting performance testing device of a hypersonic air inlet. Background technique [0002] As a key component of a scramjet engine, the hypersonic inlet has a crucial impact on the thrust performance of the engine. When the back pressure of the combustion chamber is too high, the flight angle of attack is too large, or the flight speed is too low, the hypersonic inlet may not start to flow, resulting in a large increase in the resistance of the inlet, a sharp decrease in the flow rate, and the engine will lose its energy. Thrust performance, and seriously affect the lift and drag characteristics of the aircraft. Therefore, a basic design requirement of a hypersonic inlet is to have self-starting capability. [0003] Kantrowitz has theoretically given the limit condition of the maximum area shrinkage ratio of the intake port [see Kantrowi...

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Problems solved by technology

Therefore, the validity and repeatability of this test simulation method cannot be guaranteed.

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