Document Type : Original Article
Authors
1 Space Transportation Research Institute, Iranian Space Research Center, Tehran, Iran
2 Space Transportation Research Institute, Iranian Space Research Center, Tehran, Iran,
Abstract
In this study, the pulse mode performance of a monopropellant hydrazine thruster has been studied. For this purpose, a laboratory sample of a monopropellant hydrazine thruster under atmospheric pressure was fabricated and tested. The catalyst of this thruster is synthesized natively. The pulse mode performance of this monopropellant hydrazine thruster has been evaluated experimentally and the results have been presented. The results of this study show that the monopropellant hydrazine thruster made with a synthesized catalyst produces reproducible impulses for pulses less than 10 milliseconds wide. The minimum impulse of this monopropellant hydrazine thruster is measured at 32 mNS. Also, the standard deviation of the impulse is less than 6% for 100 pulses. The thruster response time is also very reproducible. The results of this study showed that the centroid of the thruster changes linearly with the pulse width. However, the transient behavior of the chamber pressure is relatively slow, leading to a large centroid
Keywords
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