摘要
通过设计一台专用实验发动机进行试验 ,并应用参数辩识技术 ,测量确定发动机动态燃速、平均燃速、比冲等参数。通过理论分析和试验结果表明 ,该方法能准确测量性能参数 。
By using one test motor along with technique of parameter identification, multiple parameters, such as dynamic burning rate, average buring rate and specific impulse were measured. Through theoretical analysis and experimental results, this method is proved to be accurate and also has the advantages of low test cost and short experimental period.
出处
《固体火箭技术》
EI
CAS
CSCD
2000年第4期61-63,共3页
Journal of Solid Rocket Technology
关键词
固体推进剂火箭发动机
实验发动机
性能参数
solid propellant rocket engine
experimental engine +
parameter identification