Conceptual Design Model of High-Altitude Test Stand for Rocket Engines

Abstract

Conceptual design procedures and design models of HATS are revised and renewed. The results calculated using the revised method are compared with the operating conditions of HATS at the JAXA Kakuda Space Center. The previous physical method of test chamber pressure and that of ejector suction are adopted in the present model. The suction model adopts the inviscid momentum exchange mechanism. The deceleration process in the supersonic diffuser is revised using the pseudo-shock model. Physical and thermodynamic models are constructed for condensation and steam saturated flow conditions. The results calculated are in reasonable agreement with the measured values (e.g., pressure of secondary flow at the ejector section and pressure changes during engine shut down). The effect of ejector steam condensation on the operating conditions of HATS is quantitatively presented.