Solid rocket motor (SRM) for anti-tank guided weapons has a lateral rocket nozzle as a structural feature. The lateral nozzle is twisted 30 degrees in the direction of flight. Due to the structural characteristics, it generates side forces in the direction of flight. The generated side forces cause forces and moments in the entire guided weapon, affecting missile stability and accuracy during flight. Therefore, it is very important to accurately measure the force and moment during the development and production of SRM. For example, in quality specification, acceptance criteria for thrust, side force, and moment were written. This study introduced a method for measuring thrust, side force, and moment of SRM using 6- component sensor. Depending on the size of the 6-component sensor and configuration of test device, results measured in the same SRM differed. During designing of the test device, structural stability and natural frequency must be grasped, and through this, it is possible to manufacture a measuring device that does not disturb the SRM. In this study, simply purchasing a sensor with high performance for precise measurement was not the answer. Instead, the measurement accuracy was increased by properly configuring the test device to suit the measuring environment.

The performance prediction and grain burn-back analysis of rocket motor are important steps in the designing of a solid propellant rocket motor. The grain burn-back analysis of the solid grain identifies the burning surface area at each burning step in order to predict pressure-time history of the rocket motor. In this study, the shape of propellant grains was conveniently designed based on a solid modeling program of conventional purpose and the internal ballistics analysis was performed using a Matlab code which was developed to analyze the grain burn-back for this shape model. Upon carrying several analyses for rocket motors, it was confirmed that the developed code is suitable and useful.