한국형발사체 액체로켓엔진 연소기 설계의 해석적 고찰

The KSLV-Ⅱ(Korea Space Launch Vehicle-Ⅱ) which being a successor of the KSLV-Ⅰ is a space launch vehicle capable of delivering 1.5 ton-class satellite into a low earth orbit. The development of a 75 tonf-class liquid rocket engine(LRE) is planned on the basis of the technologies mastered through the preceded research of a 30 tonf-class LRE. The thrust chamber of the LRE is required to have higher combustion stability, structural integrity and thermal durability. This paper deals with the design requirements of the 75-tonf thrust chamber and a variety of technical considerations which have been conducted analytically in the course of the design for the realization of the requirements.