High-precision synchronous control device for pulse wind tunnel jet flow interference test

Abstract

The invention belongs to the technical field of hypersonic pulse wind tunnel tests, and discloses a high-precision synchronous control device for a jet interference test of a pulse wind tunnel. A jet flow system gas storage pipe of the synchronous control device is a Loudwig pipe; the quick electromagnetic valve is connected to the downstream end of the jet flow system gas storage pipe; the test model is connected with an outlet of the quick electromagnetic valve; the sensor is installed at the low-pressure section of the pulse wind tunnel close to the high-low-pressure section diaphragm. An input interface of the delay trigger is connected with the sensor; an input interface of the signal generator is connected with an output interface of the delay trigger; an input interface of the quick relay is connected with an output interface of the signal generator, and the quick relay is conducted after receiving an output signal of the signal generator; the conventional power supply is connected with the quick electromagnetic valve through a wire. When the quick relay is switched on, the quick electromagnetic valve is switched on, high-pressure gas in the gas storage pipe of the jet flow system flows out quickly, and stable jet flow synchronous with the main flow of the wind tunnel is formed on the surface of the test model.

Description

technical field [0001] The invention belongs to the technical field of hypersonic pulse wind tunnel tests, and in particular relates to a high-precision synchronous control device for jet flow interference tests in pulse wind tunnels. Background technique [0002] When high-orbit vehicles or re-entry vehicles fly at medium and high altitudes, the air density is small and the dynamic pressure is low. The traditional aerodynamic rudder control efficiency is low. The aerodynamic rudder alone cannot meet the control requirements of the aircraft. Lift reentry vehicles (such as spacecraft return capsule), lift reentry vehicles (such as space shuttle, X-37B, X-38, HTV-2, etc.) and high-speed interceptor missiles (such as PAC-3, THAAD, etc.) The engine plume and the reaction control system (RCS) replace or assist the aerodynamic rudder for control. The RCS jet flow will strongly interfere with the incoming flow, causing the peak heat flow in the jet interference area on the aircraf...

AI Technical Summary

Problems solved by technology

[0002] When high-orbit vehicles or re-entry vehicles fly at medium and high altitudes, the air density is small and the dynamic pressure is low. The traditional aerodynamic rudder control efficiency is low. The aerodynamic rudder alone cannot meet the control requirements of the aircraft. Lift reentry vehicles (such as spacecraft return capsule), lift reentry vehicles (such as space shuttle, X-37B, X-38, HTV-2, etc.) and high-speed interceptor missiles (such as PAC-3, THAAD, etc.) Engine plume and reaction control system (RCS) replace or assist pneumatic rudders for control

The RCS jet flow will strongly interfere with the incoming flow, causing the peak heat flow in the jet interference area on the aircraft surface to increase several times or even dozens of times, which brings great challenges to the aircraft surface thermal environment prediction and heat protection design.

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