A sounding rocket, also known as a research rocket, is an instrument-carrying rocket designed to take measurements and perform scientific experiments during its sub-orbital flight. This paper reports the design and fabrication of a reloadable motor with a reusable nozzle for an experimental sounding rocket. The motor can be retrieved after a flight using a parachute mechanism and hence the name reloadable. A mixture of sugar and Potassium Nitrate in a ratio of 7:13 was used as the solid propellant. The burning rate of the propellant was measured in open atmosphere and found to be 7.22 mm/s. The nozzle which is the functional part of the motor was robustly designed to yield the required thrust load for lifting the rocket. The throat diameter of the nozzle was estimated to be 8 mm corresponding to a thrust load of 688 N which could raise the rocket to an altitude of 1500 ft from the ground level. The time-dependent variation of thrust, pressure and propellant mass flow rate inside the combustion chamber was analyzed using the Meteor software. The pressure, temperature and velocity distribution within the nozzle were estimated through computational analysis using ANSYS fluent. The maximum velocity at the nozzle exit was found to be 2.86 M. Further, the cost-effective analysis of the proposed design was carried out in terms of the fuel and materials used for fabrication of the motor assembly.
Design and Development of a Cost-Effective Reloadable Motor for Sounding Rocket
Lect.Notes Mechanical Engineering
Innovative Design, Analysis and Development Practices in Aerospace and Automotive Engineering ; Chapter : 48 ; 443-450
2020-09-27
8 pages
Article/Chapter (Book)
Electronic Resource
English
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