A solid- propellant rockets key feature is its simplicity it doesnt even need a feed system. The propellant in a solid-propellant rocket is entirely contained inside the combustion chamber as one or more formed blocks known as grains, which are supported by the walls or special grids, traps, or retainer pads. The propellants are the materials that make up the chemical reactions that take place within a rocket motor.ĭepending on whether the propellant is solid or liquid, chemical rocket motors are divided into two groups. Solar radiation and nuclear reactions are two other sources of energy that can be used to propel rocket engines. The majority of the working fluid in a duct propulsion engine is its surroundings, along with some stored fuel.Ĭhemical combustion is the primary source of energy for rocket propulsion. Air-breathing engines are generally referred to as duct propulsion engines. Non- air-breathing engines are another name for rocket propulsion engines. The distinction between rocket and duct propulsion is that rocket propulsion generates thrust by ejecting stored matter (propeller). Jet propulsion is divided into two categories: rocket propulsion and duct propulsion. The act of supplying a propelled force to a body that is initially at rest, causing it to change its velocity by overcoming the retarding forces present in the medium of that body is called Propulsion. Keywords:- Solid Rocket Motor Propellant Grain Burn perimeter Star-shape grain design Later, by taking the geometrical inputs like inner radius(l), fillet radius(f), web thickness(w) for star-shaped grain having star point, n = 6, the grain area regressive is modelled by using CATIA V5 design tool. The obtained graphs for star points with different opening of star point angle in MATLAB are compared with burn perimeter values measured in CATIA V5 designing tool for corresponding set of values. A MATLAB code is written in order to plot the non-dimensional burn-perimeter (S/l) versus burnt distance (y + f)/l for star-shaped propellant grain having star point, n = 6 for = 65-75. The star-shaped propellant grain design parameter like burn perimeter by using non-dimensional equations is evaluated. Many scholars did lot of research on different sizes and shapes of grains that can provide the burn rate as per wanted. Because the thrust output as per requirement can be obtained by varying the shape of grain. Whenever, solid propellant comes into the discussion, the grain design is one of the most important topics to be studied and evaluated. GovardhanġAssociate professor, 2U.G Student, 3Head of the departmentĪeronautical Engineering, Institute of Aeronautical Engineering, Hyderabad, Telangana, India-500055Ībstract:- The main idea of my work is to discuss and evaluate the geometrical parameter like burn perimeter of the star- shaped propellant grain in detail. To Evaluate the Burn-Perimeter of Star-Shaped Propellant Grain of A Solid Rocket Motor using Dimensionless EquationsġAravind Rajan Ayagara, 2Navya Shree Veerapaneni, 3D.
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