Flow control device and method

Abstract

The invention discloses a flow control device and method. The flow control device comprises a fluid damper, an electromagnetic valve, an inspirator, a radiation fin and a catalytic bed. A fluid channel used for conducting throttling on a propellant is formed in the fluid damper. The fluid damper is connected with an inlet in one end of the electromagnetic valve. A propellant passageway is formed in the electromagnetic valve. The propellant passageway communicates with the fluid channel. The internal diameter of the propellant passageway in the electromagnetic valve is larger than that of the fluid channel in the fluid damper. The electromagnetic valve is connected with the catalytic bed through the inspirator. According to variable-section capillary tubes of the inspirator of the flow control device, by increasing the flow area of the root portions of the capillary tubes, the contamination resistance of the capillary tubes is improved, and the service life of a whole thruster is prolonged. Compared with an existing flow control device with the service life shorter than 50 hours, the service life of the flow control device can be prolonged to 500-1000 hours.

Description

technical field [0001] The invention relates to a flow control device and method, belonging to the field of thrusters. Background technique [0002] The single-component thruster uses anhydrous hydrazine as a liquid propellant. When the thruster is working, the chemical energy is converted into internal energy through the catalytic decomposition reaction of anhydrous hydrazine in the catalytic bed to form high-temperature and high-pressure gas, which works through the nozzle. Generate thrust. At present, the working life of a typical small flow (10mg / s-200mg / s mass flow) monolithic thruster is about tens of hours. One of the important factors restricting the service life is that conventional monopropellant thrusters generally use the capillary in the injector or the small holes on the injection panel of the injector to realize the flow control of the propellant. To achieve small propellant flow rates, the inner diameter of the capillary or the diameter of the small hole on...

AI Technical Summary

Problems solved by technology

[0004] (1) To achieve a small propellant mass flow rate (tens of milligrams per second of liquid propellant) through several uniformly arranged injection microholes, the diameter of each injection microhole will be small, which is difficult to process, and the parts poor consistency

[0005] (2) Small-diameter micropores are prone to clogging caused by residual soluble impurities produced by the volatilization of liquid propellants at high temperatures during long-term high-temperature ignition, and fragmentation residues produced by catalyst particles in the chemical reaction process, resulting in thruster failure, unable to achieve long-life requirements

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