Performance analysis of a Hybrid rocket for the first stage of the VEGA launcher
- Paper number
IAC-14,C4,P,16,x22677
- Author
Dr. Antonella Ingenito, University of Rome “La Sapienza”, Italy
- Coauthor
Prof. Roberto Andriani, Italy
- Coauthor
Prof. Fausto Gamma, Italy
- Coauthor
Mr. Antonio Agresta, Italy
- Year
2014
- Abstract
The development of hybrid technology has led to the design of safe, efficient, economical and low cost engines. In this paper an analysis of a hybrid rocket performance for different propellant (HTPB and paraffine) and oxidizer (O2, H2O2 and N2O) combinations has been done. Also the effect of different additives (Al, AlH3, Li, LIH) has been investigated. This analysis has shown competive performance with respect to those of solid rockets. In particular, the comparison of the specific impulse between the P80 first stage of the VEGA launcher and a paraffine/aluminum hydride hybrid engine when combined with O2, H2O2 and N2O showed an increase of respectively 19.2% , 5.8% and 3.2%, savings of up to 182 kg of propellant for the hybrid rocket. The analysis was performed using the software Rocket Propulsion Analysis. This work aims to confirm the feasibility of high-performance engines for small carriers suitable for launching nano-satellites or for the growing market of space tourism.
- Abstract document
- Manuscript document
(absent)