关键词: 固体推进剂火箭发动机;性能分析;系统识别;模拟

Abstract: The solid propellant sustainer of ZN-3 sounding rocket is a motor embedded in seven long metal fibers. The nozzle throat diameter of sustainer for flight experiment is different from the sustainer tested on the ground. In order to provide the thrust history of flight sustainer for calculating rocket trajectory, the identification simulation method of ZN-3 sustainer is presented in this paper. Firstly,the propellant basic burning rate and burning rate along metal fibers and the variation of nozzle throat diameter are determined by system identification technology according to the experimental curve (p-t) on the ground. Secondly, the nozzle thrust efficient is determined by parameter identification. Finally,the thrust history of flight sustainer is determined by interior ballistics and performance computation. The flight experimental results show that the rocket trajectory calculated is in agreement with that of ZN-3 flight experiment. It also indicates that the thrust history calculated by identification simulation is accurate. The method presented here can be applied to performance analysis of solid rocket motors.

Key words: Solid propellant rocket engine;Performance analysis;System identification;Simulation