Whole-flight liquid-oxygen input flow simulating test device for rocket engine

Abstract

The invention discloses a whole-flight liquid-oxygen input flow simulating test device for a rocket engine. The device includes a simulating tank, a conveying pipe, a flow meter, a low-temperature pneumatic ball valve, low-temperature manually-operated ball valves, a pore plate and a discharge pipe and is used for realizing whole-flight liquid-oxygen input flow simulation of the rocket engine. The simulating device uses the pressure of the simulating tank as a power and adopts the bore plate and the low-temperature manually-operated ball valves, which are connected in parallel, as flow control and adjustment elements so that demands that under different flight conditions of a pressurization system, a liquid-oxygen input flow is within a range of XX.X+-1L / s are met. In the whole-flight liquid-oxygen input flow simulating test device for the rocket engine, the liquid-oxygen discharge pipe adopts an aluminum pipe which is 200mm in drift diameter and 30m in length. During installation, an entrance of the discharge pipe is higher than an exit and the axis of the discharge pipe forms an angle of 7 degrees with the plane. The outside of the pipe is thermally insulated through polyurethane foaming so that liquid oxygen safe processing is realized and at the same time, effects of the backpressure of oxygen steam in the pipe on the input flow are reduced. The system is simple, convenient to operate, high in adjustability and low in test cost.

Description

technical field [0001] The invention relates to a liquid oxygen flow control test device, which is mainly used for the ground test of the cold helium pressurization system of the hydrogen-oxygen rocket low-temperature storage tank. Pressure conveying system test technology. Background technique [0002] my country's CZ-XX series launch vehicle X sub-stage engines use liquid hydrogen and liquid oxygen as propellants, and the pressure of the air pillow in the liquid oxygen tank is controlled by a cold helium pressure regulator. Due to the complex structure of the cold helium barometer, the difficulty in processing and comprehensive testing, and the existence of certain hidden dangers, it is difficult to meet the high-density launch requirements of this series of rockets. With the increasing maturity of low-temperature and high-pressure cold helium solenoid valve technology, a set of cold helium pressurization system composed of solenoid valve and orifice plate has been develo...

AI Technical Summary

Problems solved by technology

During the flight, the liquid oxygen is transported by the engine pump into the thrust chamber to participate in the combustion, and the pump is driven by the gas turbine. If the liquid oxygen pump on the arrow is used for the ground test, the entire test system will be very complicated, and the test operation is difficult, technical and safety risks are also high. Quite large, the development cycle of the booster system will be affected

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