Design of a Hybrid Propulsion System for Orbit Raising Applications

Details Design of a Hybrid Propulsion System for Orbit Raising Applications Design of a Hybrid Propulsion System for Orbit Raising Applications

Oct 2004

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2004esasp.557e..35b&link_type=abstract

Proceedings of the 2nd International Conference on Green Propellants for Space Propulsion (ESA SP-557). 7-8 June 2004, Chia Lagu

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A trade off between conventional liquid apogee engines used for orbit raising applications and hybrid rocket engines (HRE) has been performed using a case study approach. Current requirements for lower cost and enhanced safety places hybrid propulsion systems in the spotlight. For evaluating and design of a hybrid rocket engine a parametric engineering code is developed, based on the combustion chamber characteristics of selected propellants. A single port cylindrical section of fuel grain is considered. Polyethylene (PE) and hydroxyl-terminated polybutadiene (HTPB) represents the fuels investigated. The engine design is optimized to minimize the propulsion system volume and mass, while keeping the system as simple as possible. It is found that the fuel grain L/D ratio boundary condition has a major impact on the overall hybrid rocket engine design.

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