Simulating device for on-rocket liquid-hydrogen temperature zone cold-helium heater

Abstract

The invention discloses a simulating device for an on-rocket liquid-hydrogen temperature zone cold-helium heater and the simulating device is used for simulating the work performance of a cold-helium heater of a carrier-rocket engine. The simulating device includes devices such as a high-pressure nitrogen storage tank, a connection pipe, a reducing valve, an electromagnetic valve, a bore plate, an on-rocket heat exchange pipe, a process heat exchange pipe and an insulating layer and the like. Normal-temperature nitrogen enters an entrance of a casing after being limited in flow by the bore plate and scours the outer wall faces of the on-rocket heat exchange pipe and the process heat exchange pipe so as to carry out heat exchange. Code helium internally flows in the on-rocket heat exchange pipe and the process heat exchange pipe and carries out heat exchange with the inner wall faces of the pipes so that the temperature of the cold helium is enabled to rise to a specific value and then the helium goes to a user pipe via an exit of the process heat exchange pipe. When the temperature of helium at the exit of the process heat exchange pipe needs to be adjusted, only the opening degree of the reducing valve needs to be adjusted. The cold-helium heat exchange pipes are capable of working at a liquid-hydrogen temperature zone and the entrance temperature can be lower than 20k and when the flow of the helium is at XX-XXg / s, the exit temperature is within a range of XX-XX K. The simulating device is capable of simulating the on-rocket heater in a comparatively well manner and the exit temperature range of the low-temperature helium is adjustable and operation is simple and convenient; and the outer walls of the cold-helium heat exchange pipes are free from freezing so that the work reliability is high and cost input is low.

Description

technical field [0001] The invention relates to a low-temperature helium heating device in the liquid hydrogen temperature zone, which is mainly used for the ground test of the cold helium pressurization system of the hydrogen-oxygen rocket low-temperature storage tank, which can simulate the working performance of the cold helium heat exchange pipeline on the engine, and belongs to the low-temperature rocket storage tank Pressurized 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 in...

AI Technical Summary

Problems solved by technology

If a real gas generator and heat exchange pipe on the arrow are used for the ground test, the entire test system will be very complicated, the test operation will be difficult, and the technical and safety risks will be quite large, and the development period of the pressurization system will be affected

In China, there has not been any simulation of the effect of cold helium heating heat exchangers other than gas generators, and there is no mature experience for reference.

Images