A Study on the Design and Performance of High-altitude Simulation Test System

In order to evaluate the performance of a rocket engine on the ground, studies in a high-altitude simulation test facility are required. This paper elaborates upon the design process and evaluation of a high-altitude environment simulation facility comprising a supersonic diffuser and an ejector. The high-altitude simulation test setup was scaled down to 1/5.6 and its operating characteristics were identified through a cold flow test. Then, the target condition was achieved in a full-scale hot-flow experimental study of a liquid rocket engine. Subsequently, the performance of the proposed high-altitude simulation test system was evaluated along with its operating characteristics and techniques. The target vacuum pressure attained herein was 33.6 mbar, which approximates an altitude of 23 km.