Document Type : Research Paper

Authors

• Vahid Rahimi Ghoradel ¹
• Hossein Mahdavy-Moghaddam ²

¹ M.Sc. Student, Faculty of Aerospace Engineering, K. N. Toosi University of Technology,Tehran, ‎Iran

² Associate Professor, Faculty of Aerospace Engineering, K. N. Toosi University of ‎‎Technology,Tehran, Iran

Abstract

Each missile has a payload section and an engine section. In the path of the missile, there is a time when the mission of the engine section is over and after that the engine will not play an effective role and will be as extra weight and consequently reduced range or factor for easy detection of the warhead by enemy agents. In such a situation, after completing the engine mission, the mechanism of separating the steps and separating the head from the body is used. One of the separation methods is to use the thrust termination system method. In this paper, with the studies performed on the thrust termination system and the presentation of mathematical relations, the pressure drop and inverse thrust created in the chamber after opening the reverse thrust valves are predicted. Also, cold type separation and thrust termination system were used and the combustion chamber pressure drop is simulated. Then, the effect of important and influential factors on the thrust termination system has been investigated.

Keywords

• Reverse thrust
• Cold type separation
• Thrust termination system
• Chamber pressure drop

Main Subjects

• System Design, Space Propulsion and Space System Simulation