Droplet Vaporization/Combustion Stability-Based Design of Pre-Combustion Chambers for Hybrid Propellant Rocket Motors

Maurício Sá Gontijo, Olexiy Shynkarenko () and Artur E. M. Bertoldi
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Maurício Sá Gontijo: Aeronautical and Space Engineering Division, Aeronautics Institute of Technology, São José dos Campos 12228-900, Brazil
Olexiy Shynkarenko: Faculty of Science and Engineering Technologies, University of Brasília, Brasília 70910-900, Brazil
Artur E. M. Bertoldi: Faculty of Science and Engineering Technologies, University of Brasília, Brasília 70910-900, Brazil

Energies, 2025, vol. 18, issue 12, 1-20

Abstract: Hybrid Propellant Rocket Motors (HPRMs) have been advancing rapidly in recent years. These improvements are finally increasing their competitiveness in the global launch-vehicle market. However, some topics, such as the pre-combustion chamber design, still require more in-depth studies. Few studies have examined this subject. This work proposes a low-computational-cost algorithm that calculates the minimum pre-combustion chamber length, with a vaporization and feed-system coupled instability model. This type of analysis is a key tool for minimizing a vehicle’s size, weight, losses, and costs. Additionally, coupling with internal ballistics codes can be implemented. Furthermore, the results were compared with real HPRMs to verify the algorithm’s reliability. The shortened pre-chamber architecture trimmed the inert mass and reduced the feed-system pressure requirement, boosting overall propulsive energy efficiency by ≈ 8 % relative to conventional L*-based designs. These gains can lower stored-gas enthalpy and reduce life-cycle CO and CO 2 -equivalent emissions, strengthening the case for lighter and more sustainable access-to-space technologies.

Keywords: hybrid propellant rocket motor; pre-combustion chamber; droplet vaporization; combustion instability (search for similar items in EconPapers)
JEL-codes: Q Q0 Q4 Q40 Q41 Q42 Q43 Q47 Q48 Q49 (search for similar items in EconPapers)
Date: 2025
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