Boron-based solid fuel is considered advantageous for ducted rocket applications due to its high energy density and dual-stage combustion process.Nonetheless,its performance is constrained by the formation of a protec...Boron-based solid fuel is considered advantageous for ducted rocket applications due to its high energy density and dual-stage combustion process.Nonetheless,its performance is constrained by the formation of a protective boron oxide layer.In the current study,iron nanoparticles are incorporated into boron-based solid fuel to enhance boron's burning.Paraffin wax serves as the primary fuel and binder,while gaseous oxygen is used as an oxidizer.Four different solid fuel combinations were investigated in the experiment:pure paraffin wax,paraffin wax mixed with boron particles,and paraffin wax mixed with boron alongside 10%and 20%iron particles.The main effort of the research is to assess their combustion characteristics,focusing on regression rate and combustion efficiency.While the inclusion of 10%iron particles resulted in a decrease in the regression rate,it led to an improvement in combustion efficiency by reducing the residual active boron content in the condensed combustion product by~60%.Furthermore,it was observed that increasing the proportion of iron particles to 20%further enhanced combustion efficiency to approximately 4%.The entire assessment has been carried out using a lab-scale hybrid propellant ducted rocket motor configuration having an inlet duct on regenerative concept with the secondary combustor.In the present investigation oxygen is injected both in the primary and the secondary combustor,whereas in the existing actual/lab-scale ducted rockets,an energized air is introduced in the secondary combustor.It serves as an economical system for the preliminary investigation of solid fuel impregnated with boron particles.It is expected that the present study could prove valuable strategies for future applications of boron-based hybrid propellants in ducted rocket systems.展开更多
基金the Centre of Excellence in Propulsion Systems,Alliance University,Bangalore,for providing funds(Grant No.-AU/DeanR/RC/2022)。
文摘Boron-based solid fuel is considered advantageous for ducted rocket applications due to its high energy density and dual-stage combustion process.Nonetheless,its performance is constrained by the formation of a protective boron oxide layer.In the current study,iron nanoparticles are incorporated into boron-based solid fuel to enhance boron's burning.Paraffin wax serves as the primary fuel and binder,while gaseous oxygen is used as an oxidizer.Four different solid fuel combinations were investigated in the experiment:pure paraffin wax,paraffin wax mixed with boron particles,and paraffin wax mixed with boron alongside 10%and 20%iron particles.The main effort of the research is to assess their combustion characteristics,focusing on regression rate and combustion efficiency.While the inclusion of 10%iron particles resulted in a decrease in the regression rate,it led to an improvement in combustion efficiency by reducing the residual active boron content in the condensed combustion product by~60%.Furthermore,it was observed that increasing the proportion of iron particles to 20%further enhanced combustion efficiency to approximately 4%.The entire assessment has been carried out using a lab-scale hybrid propellant ducted rocket motor configuration having an inlet duct on regenerative concept with the secondary combustor.In the present investigation oxygen is injected both in the primary and the secondary combustor,whereas in the existing actual/lab-scale ducted rockets,an energized air is introduced in the secondary combustor.It serves as an economical system for the preliminary investigation of solid fuel impregnated with boron particles.It is expected that the present study could prove valuable strategies for future applications of boron-based hybrid propellants in ducted rocket systems.
