مقاله (118055)
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کد پروژه: 127605
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🔢 کد پروژه: 118055
📌 عنوان پروژه: مقاله
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Structural and Operational Optimization of Satellite Launch Vehicles: Transitioning from Bipropellant to Liquid Monopropellant Systems
Author: Amir Karamollachaab
Affiliation: Independent Aerospace & Green Propulsion Researcher
Abstract
This study evaluates the structural, mass fraction, and operational trade-offs involved in transitioning small-to-medium satellite launch vehicles and orbital stages from conventional dual-tank bipropellant systems to single-tank liquid monopropellant propulsion architectures. While bipropellant configurations inherently deliver superior specific impulse (IspIsp), their architectural complexity—characterized by redundant fluid networks, cross-coupling valves, and separate pressurization lines—imposes a severe structural mass penalty and increases single-point failure modes. Utilizing analytical mass budgeting and parametric sizing models, this paper demonstrates that adopting a high-performance liquid monopropellant architecture achieves an immediate 50% reduction in propellant tank count and approximately a 25% reduction in dry structural mass. Although this transition involves a moderate specific impulse trade-off, the net payload mass delivery across short-burn, dedicated orbital insertion, and rapid-response launch missions shows marked operational improvement. The paper provides a comprehensive engineering framework comparing tankage efficiency, feed-system complexity, and catalytic chamber dynamics, while identifying key critical path requirements in catalyst thermal management and multiphase decomposition modeling.
۱. Acta Astronautica (انتشار توسط آکادمی بینالمللی فضانوردی)
۲. Journal of Propulsion and Power (انتشار توسط AIAA)
۳. Aerospace Science and Technology (انتشار توسط الزویر)
۴. Journal of Spacecraft and Rockets (انتشار توسط AIAA)
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