Numerical and experimental analysis of hydroxyl-terminated poly-butadiene solid rocket motor by using ANSYS

Abstract

Solid rocket motor plays a crucial role in rocketry. Solid rockets are in widespread use nowadays, not only for space purposes but also for the development of missiles and sounding rockets. These solid rocket engines work in accordance with Newton law principles. Launch vehicle consists of several stages, each stage being either Solid Rocket Motor or Liquid Rocket Engine. A phased market research methodology was used in this experiment to develop a solid rocket motor for a space rocket. The purpose of the study was to provide insight into the susceptibility of the changing properties of the solid rocket engine and the impacts arising from that approach. In previous instances, a 2 m diameter HTPB solid rocket motor is used to propel a load of 3800 kg, producing a thrust of 120 KN, a specific impulse of 220 s and a traveling duration of 110 s. The thrust needed for the motor is attained after ignition at a delay of 3 s. A next generation of solid rocket motor HTPB should be designed to generate a 199.3 KN thrust and should generate the required thrust at the start of ignition. The modelling is done in CATIA software and areas are calculated in software itself and the model obtained from the design parameters is subjected to stress, strain and deformation analysis in ANSYS software. The main constraint is to have the same diameter and length, with even better performance as well.