Technological advancements in the HYPROB Project - Demonstrators development line

Paper number

IAC-18,C4,5,7,x47108

Author

Dr. Francesco Battista, Italy, CIRA Italian Aerospace Research Centre

Coauthor

Dr. Daniele Ricci, Italy, CIRA Italian Aerospace Research Center, Capua

Coauthor

Mr. Daniele Cardillo, Italy, CIRA Italian Aerospace Research Center, Capua

Coauthor

Dr. Pasquale Natale, Italy, CIRA Italian Aerospace Research Center, Capua

Coauthor

Mr. Manrico Fragiacomo, Italy

Coauthor

Dr. Vito Salvatore, Italy, CIRA Italian Aerospace Research Center, Capua

Coauthor

Dr. Michele Ferraiuolo, Italy, C.I.R.A. - S.C.P.A.

Year

2018

Abstract

The activities, described in the present paper, have been conducted in the framework of the HYPROB Program, carried out by the Italian Aerospace Research Centre (CIRA) under contract by the Italian Ministry of Research (MIUR). The Program has the main objective to enable and improve National system and technology capabilities in the field of liquid rocket engines (LRE) for future Space Propulsion Systems and applications, with specific regard to LOX/LCH4 technology. Moreover, the Program is in coherence with the long-term vision, provided by the Italian Space Agency (ASI) on Space Propulsion.
According to the last implementation of the program, a system line, named “HYPROB-DEMONTRATORS”, has been included: it aims at designing, manufacturing and testing LRE demonstrators, LRE and HRE breadboards. 
The main objective of this line is to design, manufacture and test a regeneratively cooled LOX/LCH4 demonstrator, a pressure-fed thrust chamber assembly (TCA), aiming at validating critical design and technology features and then assessing the technology readiness level of potential solutions for future engines. 
The present paper illustrates the advancements in the technological activities in the development line. 
The activities, related to the development of the HYPROB LOX/LCH4 Demonstrator are described and the current status discussed. Recently relevant advancements have been achieved on the Injector Head manufacturing and testing. In fact, after the ordinary acceptance and functional tests, HYPROB IH was mounted on a dummy chamber, developed by AVIO, and a successfull firing test campaign was accomplished. On the path of consolidating the technological aspects for the final demonstrator manufacturing, a 1:1 scale mock-up has been manufactured  by means of electro-plating technology and passed  leak and proof tests. In order to furtherly deepen the comprehension of high pressure combustion issues and heat load distribution inside a LOX/GCH4 thrust chamber, a calorimetric breadboard (SSBB) has been designed and actually is in manufacturing phase. Thus, the development status of both SSBB and final demonstrator is presented and main results discussed.

Abstract document

IAC-18,C4,5,7,x47108.brief.pdf

Manuscript document

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