Theoretical study on the primary combustion of the boron-based fuel-rich propellant for solid rocket scramjet

Key Points

• Combustion characteristics of boron-based fuel-rich propellant were analyzed, aiming to improve rocket propulsion.
• Theoretical models indicate enhanced efficiency during the combustion phase for solid rocket scramjets.
• Analysis of the combustion properties focused on fuel-rich mixtures, aiming to optimize performance.
• This work suggests critical insights into combustion dynamics; further experimental validation is needed.