Investigation on Performance Characteristics of Hydrazine Monopropellant Thruster according to Reaction Chamber Adiabatic Temperature

In this paper, by creating and developing a code based on thermodynamics and gas dynamics equations, the performance characteristics of a 1N hydrazine monopropellant thruster such as thrust force, specific impulse, characteristic exhaust velocity, and propellant mass flow rate have been studied theo...

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Hlavní autoři:	Seyyed Rashad Rouholamini, Mohammad Ali Amirifar, Alireza Rajabi, Nooredin Ghadiri Massoom
Médium:	Artigo
Jazyk:	Persa
Vydáno:	Aerospace Research Institute 2022-09-01
Edice:	فصلنامه علوم و فناوری فضایی
Témata:	monopropellant thruster hydrazine ammonia dissociation rate performance characteristics reaction chamber temperature
On-line přístup:	https://jsst.ias.ir/article_143736_47f9de12e225fc5dcadaf340f5d9d6d9.pdf
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