Document Type : Research Paper
Authors
1 Aerospace Department of Aerospace Engineering Malek Ashtar University of Technology, Tehran, Iran
2 Associate Professor, Aerospace Department of Aerospace Engineering Malek Ashtar University of Technology, Tehran, Iran
3 Assistant Professor, Satellite & amp; amp, LV center, Aerospace Department, Malek Ashtar University of Technology, Tehran, Iran
Abstract
A new approach to the design and development of launchers is the use of advanced technologies to reduce design and development costs as much as possible. In this paper, an approach to reduce costs and increase reliability is proposed, which is based on the use of a non-turbo pump propulsion system (pressure-fed propulsion system) instead of a turbo pump propulsion system. For this purpose, the multidisciplinary conceptual design optimization of a two-stage launch vehicle with a pressure-fed propulsion system with the aim of sending max payload with a least gross mass to the orbit (500 km) in terms of structure, aerodynamics, propulsion, pressure vessels, simulation, and pitch program disciplines. Then, the sensitivity analysis was performed on the optimum launcher to determine the efficiency of the launcher at different orbital heights and the ability to carry a suitable payload.
Keywords
- Launcher
- Propulsion system
- Pressure-fed system feeding
- Multidisciplinary design optimization
- Sensitivity analysis
Main Subjects
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