摘要
为获得延伸喷管展开特性参数,根据实际测得的延伸锥展开各种摩擦阻力之和,利用分析力学及数值分析有关理论对延伸喷管进行展开动力学分析与计算。计算得到的展开位移和试验测得的展开位移曲线吻合,展开时间和试验值相比误差仅为4.7%。分析计算对延伸喷管技术研究具有重要参考价值,为延伸喷管展开机构的改进提供了重要的理论依据。
The extending displacement, velocity and acceleration and internal pressure of the actuator of a solid rocket motor （SRM） extendible exit cone （EEC） nozzle were calculated. Firstly, the nozzle was reduced to a one degree-of-freedom dynamic system, and then the dynamic equations describing the extending process of the nozzle were derived using the theory of analytical mechanics. The equivalent axial resistance was determined through experiment. After solving the dynamic equations, these dynamic parameters were obtained, which agree well with the experiment.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2008年第1期37-42,共6页
Journal of Propulsion Technology
关键词
固体推进剂火箭发动机
延伸喷管
数值仿真
性能参数
Solid propellant rocket engine
Extendible exit cone nozzle
Numerical simulation
Performance parameter
