In the era of cryogenic propellants with high specific impulse; under microgravity situations, long-term storage and higher energy thruster management are highly needed. As methane is a reasonable cooling membrane for radiation and ablation chambers so high LOX/LCH4 combustion efficiency and reliable spark ignition to be achieved to develop a methane engine. To maintain the thermocouple system in the spacecraft and to prevent outer harmful radiation in space, the respected agencies may use thick-walled propellant containers with high pressure. To check the feasibility and effectiveness of a subcooled cryogenic propellant, a combination of pump depressurization as active cooling and liquid choke evaporation as passive cooling has been proposed and analyzed.

Acoustic emission testing is one of the most common and effective non-perishable test methods that allow testers to collect data and provide accurate propellant results. Acoustic discharge occurs when an object is under pressure or due to holding a heavy load or from extreme temperature changes, heat stress, cold cracks, melting, bond failure, and fiber are sources of acoustic discharge. The sensors used to record acoustic emissions use piezoelectric material. The effects of various parameters on the combustion rate of solid propellants are discussed and reviewed. The preferred method of overheating heat reduction techniques is acoustic extraction as it is very simple, fast, expensive, and can be performed with 98% accuracy. However, with a more accurate burn rate using BEM. BEM, however, requires a large amount of propellant. So, in everyday practice, the acoustic extraction method is well used by geothermal scientists worldwide. The craw ford bomb is the oldest method of temperature measurement, the only one that is most suitable for double base propellants with an accuracy of 97 to 98%. Advanced technologies such as closed bombs, ultra-noise measurement, microwave, x-ray, and plasma power, etc. While the chimney-type laser method is very complex but naturally boring further with various diagnostic methods such as x-ray, method of -flash, and pressure. The capture method, the servo method measurement method, and the high-speed motion detection method to determine erosion are also important. Literature ReviewGarima Gupta et.al studied the combustion rate of solid propellants, whether stable or solid, under a variety of conditions operating conditions are very important for the use and application of important reasons. The average burnout rate is web

Experimental sounding rockets are important contributors to aerospace engineering research. However, experimental-sounding rockets are rarely used for student research projects by institutes in India. The unavailability of rocket motors, which require complex machining and explosive propellants, is a major barrier to the use of sounding rockets in student research projects. We ran into this problem while developing a sounding rocket motor for project and learning purposes. The project focuses on designing and constructing a solid rocket motor that researchers can use as the primary propulsion unit in experimental sounding rockets. Initially, basic designs were evaluated, as various concepts of observations of propellant configuration. The accessibility and ease of use of manufacturing and casting of propellants played a significant role in determining the best propellant based on these findings, the theoretical values for combustion chamber parameters were obtained. Also, materials were chosen accordingly, and a fundamental small-scale experimental design was built and extensively tested. This small-scale motor was created by combining all of the analysis and theoretical data.At experimental testing, we got to know the thrust generated is 763.47N and the motor runs for 4.1 sec, the total mass of the propellant is maxed at 1500g which gives us the max mass flow rate of 0.65Kg/sec this is the output for our solid rocket motor.