Design And Experiment Of The Solid Rocket Motor With Thrust Termination Devices

Guidenization of conventional rocket is one of the important development directions of precision guided ammunition and also the development trend of weapon modernization.Study of long-range,high-thrust solid rocket engines with limited weight,volume and cost will have positive significance to guidenization of the conventional rockets.In addition in order to obtain stable ballistic characteristics,adopting the thrust termination devices at a preset time to achieve thrust termination,which in turn to separate rocket engine,will greatly improve the control efficiency of guided rocket.In this paper,a research has been made on solid rocket motor of a type guided rocket.The launch and booster function of the guided rocket was well achieved.And at preset ballistic position with the thrust termination devices,the separation of the first stage and the second stage of the rocket was realized.According to the requirement of the projectile in general,analysis was made on the structure and performance of the motor and thrust termination devices.And the design was determined,with theoretical calculation.Through processing and preproduction of the design,the motor and thrust termination devices were produced.Corresponding flight tests was taken on the ground and in the range.During the tests,the guided rockets were successfully launched and were taken into the preset trajectory.Then at the preset point,the thrust termination of the engine was realized,and the separation of the guided rocket was successfully achieved.The engineering development of solid rocket engine with thrust termination device is realized.It provides a reference for the application of this technology in other products.The result of the tests shows that this design basically meets the requirements of the tactical and technical indexes in general.Due to the manufacturing accuracy error,the difference between the selected propellant parameters and the design value and other factors,there is a certain difference between the test result and the design calculation value.This paper in depth discusses and analyzes the test results,analyzes the causes of differences,offers measures to improve engine combustion chamber pressure such as appropriately increasing the propellant burning rate,decreasing the throat diameter and so on,can further improve the work efficiency of the solid rocket motor,and lays the foundation for subsequent engineering development of the guided rocket.