TY - JOUR
TI - Experimental study on composite solid propellant material burning rate using algorithm MATLAB
AU - Thunaipragasam Selvakumaran
AU - Natarajan Kadiresh
JN - Thermal Science
PY - 2016
VL - 20
IS - 14
SP - 1119
EP - 1125
PT - Article
AB - In rocketry application, now-a-days instead of monopropellants slowly  composite propellants are introduced. Burning rate of a solid state composite  propellant depends on many factors like oxidizer-binder ratio, oxidizer  particle size and distribution, particle size and its distribution, pressure,  temperature, etc. Several researchers had taken the mass varied composite  propellant. In that, the ammonium perchlorate mainly varied from 85 to 90%.  This paper deals with the oxidizer rich propellant by allowing small  variation of fuel cum binder ranging from 2%, 4%, 6%, and 8% by mass. Since  the percent of the binder is very less compared to the oxidizer, the mixture  remains in a powder form. The powder samples are used to make a pressed  pellet. Experiments were conducted in closed window bomb set-up at pressures  of 2, 3.5, and 7 MN/m2. The burning rates are calculated from the combustion  photography (images) taken by a high-speed camera. These images were  processed frame by frame in MATLAB, detecting the edges in the images of the  frames. The burning rate is obtained as the slope of the linear fit from  MATLAB and observed that the burn rate increases with the mass variation of  constituents present in solid state composite propellant. The result  indicates a remarkable increase in burn rate of 26.66%, 20%, 16.66%, and  3.33% for Mix 1, 2, 3, 4 compared with Mix 5 at 7 MN/m2. The percentage  variations in burn rate between Mix 1 and Mix 5 at 2, 3.5, and 7 MN/m2 are  25.833%, 32.322%, and 26.185%, respectively.