Conceptual design and optimization of a small launch vehicle with practical considerations

Abstract

Using technologies that are based on space missions became an essential part of our lives. Space systems provide a lot of services to us in many different applications. To maximize the benefit of space missions and launch more missions, we need the link between the Earth and space, which is provided by a launch vehicle. The demand for launch vehicles has been continuously increasing, and many players are competing in the global launch service market. This study explores a framework for conceptual design/optimization of a small satellite launch vehicle. The needs analysis and justifications for a national launch vehicle research and development (R&D) program are conducted, reflecting various perspectives (e.g., development options – private-led versus government-led, attracting talents, job creation, market creation, technology spill-over). Requirement definition and subsystem analysis have been conducted following a systems engineering process, and the launch site option has been explored. A conceptual design/optimization procedure for a launch vehicle considering practical issues (e.g., thrust to weight ratio of an engine, initial acceleration of each stage) is developed by integrating the optimal staging and the trajectory optimization modules. A case study on the development of a launch vehicle for the United Arab Emirates demonstrated the effectiveness of the developed procedure.