Turbopump propulsion systems have been used in almost all launch vehicles. With the advancement of manufacturing technologies, especially in the use of composite and lightweight structures, the use of non-turbopump propulsion systems has been considered due to the reduction of operating costs. This study has been investigated the multi-disciplinary optimization design of a two-stage launch vehicle using a pressure-fed propulsion system for both stages. Two main propulsion systems including gas-pressure and self-pressure feeding systems, have been evaluated in different configurations on two launcher stages. To extracting the optimum and possible solution, the launcher mission also has been added as a design variable in the optimization algorithm. The launcher has been extracted and introduced for each specific configuration of the launcher to achieve a certain orbital altitude with the maximum carrying payload and minimum gross mass. For this purpose, the AAO multidisciplinary optimization design framework has been used. The system-level and subsystem optimizer of the GA-SQP algorithm have been chosen.
Multi-Disciplinary Optimization Conceptual Design of the Launcher Based on Non-Turbopump Propulsion Systems
2022
Aufsatz (Zeitschrift)
Elektronische Ressource
Unbekannt
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