Exhaust process simulator of safety valve on rocket

A technology of exhaust process and simulating device, which is applied in the direction of measuring device, engine test, machine/structural component test, etc. It can solve the problem of limited number of normal working times of movable parts and seals, and improve the level of human-computer interaction. , improve adaptability, improve the effect of system utilization

Inactive Publication Date: 2014-10-29
BEIJING INST OF AEROSPACE TESTING TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Compared with other industrial valves used in ground tests, due to the special requirements for the use of low-temperature safety valves, the number of times the movable parts and seals can work normally is very limited

Method used

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  • Exhaust process simulator of safety valve on rocket

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Embodiment Construction

[0013] Such as figure 1 As shown, the present invention mainly consists of a program controller 2, a data acquisition processor 3, a cable 4, a pressure sensor 5, a low-temperature pneumatic valve 6, a connecting pipeline 7, an orifice plate 8, a two-position five-way solenoid valve 9, and a pressure reducing valve. 10. The nitrogen cylinder is composed of 11. Among them, the program controller 2, the data acquisition processor 3, the cable 4, and the pressure sensor 5 form the pressure measurement and command generation system of the propellant tank 1; the exhaust gas flow is limited by the orifice plate 8; Road 7, solenoid valve 9, decompression valve 10 and nitrogen cylinder 11 form instruction execution mechanism.

[0014] During the work of the present invention, at first in the data acquisition processor 3, setting safety valve return seat pressure is P min , the opening pressure is P max ; The pressure sensor 5 perceives the pressure value of the propellant tank 1 as...

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Abstract

The invention discloses an exhaust process simulator of a safety valve on a rocket. The simulator is used for a ground test of a cryogenic rocket engine or dynamical transport system. A program controller, a data acquisition processor and a pressure transducer form a propellant tank pressure measurement and instruction generation system. According to needs, safety valve reseating pressure is set as Pmin, opening pressure is set as Pmax, a perceived propellant tank pressure value is set as P, and an on/off digital instruction is generated according to the relationship of the above three values. A cryogenic pneumatic valve and an orifice plate form an instruction execution system for executing blow-off opening or closing movement. It can be guaranteed that pressure P is less than or equal to Pmax and greater than or equal to Pmin during pressurization process. If a safety valve is applied to a propellant tank for high-temperature gas pressurization, it is only required to replace a cryogenic pneumatic valve with a valve capable of operating in a high-temperature gaseous environment. According to the invention, equipment technology is mature; system reliability, adaptability and utilization rate are enhanced; equipment and maintenance costs are minimized; and the human-computer interaction level is improved.

Description

technical field [0001] The invention relates to an intelligent control exhaust device, which is mainly used for the ground test of a low-temperature rocket engine or a pressurized conveying system, and can simulate the exhaust working process of a safety valve of a low-temperature storage tank on an arrow, belonging to the low-temperature rocket power system test technology. Background technique [0002] my country's CZ-XX series launch vehicle X-stage engines and the new generation of launch vehicle main power engines all use liquid hydrogen and liquid oxygen as propellants. In order to reduce the structural quality of the storage tank and improve the payload of the rocket, the internal pressure bearing capacity of the propellant storage tank is designed All adopt a small redundancy factor. In order to ensure the safety of the storage tank during the whole process from the low-temperature propellant filling to the end of the flight, and prevent the storage tank from overpress...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M15/02
Inventor 赵耀中尹奇志瞿骞刘玉涛刘海生尚宇王森王永超董少斐王鹍葛绍岭王璐
Owner BEIJING INST OF AEROSPACE TESTING TECH
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