The propulsion system of a projectile is very important for the aerospace industry. To perform space exploration mission, controlling position and posture of the projectile in the terminal stage is very important. In this study, a new lateral thrust system is proposed to control the position and posture of the projectile at the terminal stage. Based on nozzles in a lateral thruster, a high-speed projectile can instantly change its position and posture. After changing its position and posture, reverse thrust is generated to control unnecessary movements for stabilizing. Based on various tests, the operation and performance of the nozzle opening device (NOD) of the separation mechanism were validated. As a result, excellent reproducibility was confirmed with standard deviation of 0.057 ms for the time from the end of igniter operation to the start of NOD separation. The internal pressure of the chamber and NOD separation time were inversely proportional to each other with a linear relation. The internal pressure of the chamber and flight speed of NOD were also proportional to each other. The flight speed of NOD was 37.53 m/s at the maximum expected operation pressure (β), 30.26 m/s at 0.5 β, and 17.05 m/s at 0 psi.

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.