Liquid-hydrogen temperature zone vibration test heat insulation method for cold-helium pressurization system of rocket tank

Abstract

The invention discloses a liquid-hydrogen temperature zone vibration test heat insulation method for a cold-helium pressurization system of a rocket tank. Adopted devices and materials are mainly a stainless-steel box, support fasteners, a polyurethane heat insulating material and electromagnet protective covers. The implementation process of the method is as follows: the stainless-steel box is installed on a horizontal slide platform of a vibration platform; the support fasteners are installed in the stainless-steel box; specific installation distances from all elements of the pressurization system and the center of a pipe to the bottom part of the stainless-steel box are ensured and the surfaces of the pipe and the elements of the pressurization system are each wrapped with a layer of plastic film; the electromagnet protective covers cover cold-helium electromagnetic valves and then the stainless-steel box is filed with the polyurethane heat insulating material and after the heat insulating material is cured, the electromagnet protective covers are taken out; and after heat dissipation of the heat insulating material is completed, a vibration test heat insulating protection work of the pressurization system is completed. Overall heat insulating processing is carried out on the pressurization system so that installation and operation of the system are facilitated and a heat insulating processing procedure of system elements is simplified so that a system heat insulating effect is improved and contact of the vibration platform with low-temperature media is prevented and at the same time, heat dissipation demands in a work process of electromagnets of the cold-helium electromagnet valves.

Description

Technical field [0001] The invention relates to an adiabatic protection method for the vibration test of a liquid hydrogen temperature zone of a rocket booster sub-system, which is mainly used for the insulation of test system components and the low temperature protection of a vibrating table, and belongs to the low temperature system heat insulation technology. Background technique [0002] my country's CZ-XX series carrier rocket X-stage engines use liquid hydrogen and liquid oxygen as the propellant, and the pressure of the liquid oxygen tank air pillow is controlled by a cold helium pressure regulator. Because the cold helium pressure regulator has a complex structure, is difficult to process and comprehensively detect, and has certain hidden troubles, it is difficult to adapt to 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 cold helium pressurization s...

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Problems solved by technology

Since only the low-temperature vibration test of the valve single body was carried out in the early stage, there is no mature experience on how to insulate the booster system and low-temperature protection of the shaking table system in the system-level vibration test.

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