Research Projects

The development of high-energy-density fuels is imperative for the next generation of propulsion systems, especially in aerospace applications. Strained cage hydrocarbons such as Cubane, Methylcubane, and Bishomocubane (BHC) derivatives—including Bis(nitratomethyl)-1,3-bishomocubane (DNMBHC) and diazido-dimethyl-bishomocubane (DADMBHC) offer unique advantages due to their high volumetric energy content, higher specific impulse, and favorable thermodynamic properties. These compounds are potential candidates to replace conventional hydrocarbons like RP-1 (refined kerosene) in liquid rocket propellant formulations. Despite these advantages, their practical application in propulsion systems remains largely unexplored due to limited synthesis yields and lack of performance data under realistic combustion conditions. This project aims to bridge that gap by investigating the first-ever comprehensive spray combustion characteristics of high-energy bishomocubane-based novel propellants under high-pressure, oxygen-rich conditions using advanced diagnostics. To aid this, advanced diagnostics like particle image velocimetry (PIV), shadowgraphy, and color ratio pyrometry (CRP) are employed. The rationale stems from earlier ISRO’s work, who successfully synthesized similar compounds and conducted preliminary droplet combustion studies. However, spray combustion—more representative of real engine conditions—remains untested. This project bridges the gap between lab-scale spray studies and real-engine conditions, paving the way for potential application in liquid rocket propulsion systems. The goal is to generate comprehensive spray combustion, and emission profiles that can enable optimization and scale-up for semi-cryogenic and scramjet engines. The hypothesis to be tested is that the unique structural and energetic properties of cage hydrocarbons will result in higher flame temperatures and energy release, albeit with potentially increased soot formation due to their cyclic nature. Additionally, the project aims to confirm their miscibility and combustion compatibility with RP-1 surrogates, paving the way for blended applications. Key experiments include: • High-pressure spray characterization using PIV and shadowgraphy. • Combustion tests in a constant volume combustion chamber at pressures up to 50 bar. • Temperature and soot mapping using High speed camera-based CRP. • Emission profiling using gas analyzers. If successful, this research will significantly advance the fundamental understanding of high-density propellant combustion and provide actionable data for scaling up fuel synthesis and motor-level testing. It will also offer a robust diagnostic framework for characterizing future energetic materials. From an application standpoint, this work aligns with India's strategic goals in aerospace and defense, offering a pathway for indigenous development of next-generation rocket propellants with superior energy efficiency and performance.