Design of an Upper Stage Propulsion System by Multi Objective Hybrid PSO

Nosratollahi, Mehran; Fatehi, Mohammad Fatehi; Adami, Amirhossain

doi:10.30699/jsst.2020.1101

Document Type : Research Paper

Authors

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

² PhD Candidate, Shahid Beheshti University, Aerospace Department, Tehran, Iran

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

https://doi.org/10.30699/jsst.2020.1101

Abstract

Orbital transfer blocks has the task of transferring satellites to objective orbits from parking orbit. In this paper, Attention will be given to multidisciplinary optimal design of the propulsion system of two liquid component which is one of the most important subsystems of Orbital transfer blocks. Designing with multi objective bipropellant system, based on minimum total mass and maximum Isp, and at the end mentioned to costs and compared. For combinations of NTO as Oxidizer and fuels which are: UDMH, MMH, Hydrazine and RP-1 then for usual structures that utilized in this systems, design and optimization occurred by multi objective hybrid Particle Swarm Optimization (PSO) algorithms.

Keywords

20.1001.1.20084560.1399.13.3.1.5

Main Subjects

System Design, Space Propulsion and Space System Simulation

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Design of an Upper Stage Propulsion System by Multi Objective Hybrid PSO

References

References

[1] Nosrattollahi, M., Basohbat Novinzadeh; A.R., Zakeri; M., Bemani; V. and Emadi Noori, Y., “Integrated Design of Orbital Transfer Block in an Optimized and Multistep Converged Environment,” Journal of Space Science and Technology, Vol.7. No. 4, Winter 2015, pp. 27 -37.

Volume 13, Issue 3 - Serial Number 44September 2020Pages 1-16

Volume 13, Issue 3 - Serial Number 44
September 2020
Pages 1-16