A two-stage solenoid valve for high-precision pressure control of small flow

Abstract

The invention discloses a double-stage electromagnetic valve for high precision pressure control of micro small flow. An inlet connector, an outlet connector, a first electromagnetic valve body, a connection ring and a second electromagnetic valve body are included; the inlet connector is connected with one end of the first electromagnetic valve body; the other end of the first electromagnetic valve body is connected with one end of the second electromagnetic valve body through the connection ring; the other end of the second electromagnetic valve body is connected with the outlet connector; and the first electromagnetic valve body and the second electromagnetic valve body are symmetrical about the center vertical line of the connection ring. According to the double-stage electromagnetic valve for high precision pressure control of micro small flow, the two stages of electromagnetic valve bodies completely same in structure are adopted to be arranged back to back in a series connectionmanner, and it is achieved that the gas capacity volume between the two stages of valve bodies is accurately controllable; and by controlling the work time sequence of the two stages of electromagnetic valve bodies, the functions that high pressure and low pressure of a work area are reliably isolated and pressure is accurately controllable are effectively achieved.

Description

technical field [0001] The invention belongs to the technical field of spacecraft space fluid management, and in particular relates to a two-stage solenoid valve for small flow and high-precision pressure control. Background technique [0002] DFH-3B platform and DFH-5 satellite platform system, in order to ensure the stable and reliable operation of the electric thruster on orbit, require the storage and supply subsystem to meet the on-orbit working pressure of 0-15MPa, and the pressure output accuracy of the pressure control unit is better than ±3%. The output pressure range is 0.15~0.3MPa, the output decompression ratio is ≥45, the output flow rate is 0~10mg / s, and the high and low pressure areas of the system are reliably isolated during the working period, and cannot be directly connected. [0003] The core component of the conventional mechanical decompression method used in the propulsion system is the mechanical decompressor. First of all, the decompression ratio of ...

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Problems solved by technology

[0003] The core component of the conventional mechanical decompression method used in the propulsion system is the mechanical decompressor. First of all, the decompression ratio of the mechanical decompressor in the domestic space propulsion system is about 20:1, and at the same time, it does not meet the requirements of high precision under the condition of small flow. The output requirements and the external leakage of a single unit do not meet the 15-year working requirements of the electric propulsion storage and supply unit; moreover, once the mechanical decompression method is calibrated in the ground test, the pressure working point cannot be adjusted on the orbit, nor can it meet the subsequent changes. Working condition mode and possible propulsion system failure emergency mode work requirements; finally, the essence of mechanical decompression is throttling and decompression. In the mode of large decompression ratio and small flow output, there will generally be a two-phase flow state. In this case It is a fatal hazard for the electric propulsion storage and supply system

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