Research Projects

space technology is constantly evolving, and the demand for small satellites is expected to grow significantly in the coming years. Research focuses on finding more efficient, reliable, lighter, and less expensive components. The mass of a satellite's mass consists of propellant needed for orbit insertion and attitude control. Improvements in engine efficiency increase the allowable payload in direct proportion to propellant savings. Oxidation-resistant coatings and cooling processes are employed to overcome limitations in combustion chamber development. A typical liquid bi-propellant engine is a disilicide-coated niobium alloy (C-103) chamber employing nitrogen tetroxide (N2O4) and mono methyl hydrazine (MMH). To improve engine performance, new combustion chamber materials should be able to withstand higher temperatures and reduce or eliminate fuel film cooling. A material system composed of a Rhenium (Re) substrate and Iridium (Ir) has provided a high-temperature capability for low-thrust chambers. The Chemical vapor deposition (CVD) process is currently the most established process for fabricating Ir or Re chambers. The Make in India mission aims to develop thrust or combustion chambers with oxidation resistant Ir-Re coatings and validate the performance of indigenously developed chambers using association with IsRO and industry.