Authors

1 Aerospace University Complex, Malek Ashtar University of Technology, Tehran, Iran

2 Department of Aerospace Engineering, Malek Ashtar University of Technology, Tehran, Iran.

3 Satellite & LV center, Aerospace Department, Malek Ashtar University of Technology.Tehran.IRAN

Abstract

The hydrazine propulsion system is one of the most widely used monopropellant
propulsion systems. This low-cost and low mass system is used for the attitude control of
satellites due to its high specificity and rapid response.For this purpose, in the present
study, an optimal design of a hydrazine monopropellant propulsion system with the aim of
minimization of total mass and maximization of total impulse in the framework of
multidisciplinary design optimization and sequential design method is considered. In
addition, the principles of multidisciplinary and sequential design are described in this
paper. It has been tried to examine the impact of different elements on design goals and
compare the optimal value obtained in each of the design structures from different
aspects. It should be noted that the design process is accomplished in two ways, i.e.
single-objective and multi-objective, and the optimal multidisciplinary design method is
compared with the sequential design method for the hydrazine monopropellant propulsion
system.

Keywords

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