固体火箭发动机延伸喷管展开动力学分析

推进技术 ›› 2008, Vol. 29 ›› Issue (1): 37-42.

固体火箭发动机延伸喷管展开动力学分析

尤军峰,校金友,张铎,甘晓松,任全彬

西北工业大学航天学院陕西西安710072;西北工业大学航天学院陕西西安710073;西北工业大学航天学院陕西西安710074;西北工业大学航天学院陕西西安710072;陕西动力机械研究所;陕西西安710025;陕西动力机械研究所;陕西西安710025

发布日期:2021-08-15

Dynamic analysis on extendible exit cone nozzle of solid rocket motor during extending

Coll.of Astronautics,Northwestern Polytechnical Univ.,Xi’an 710072,China;Coll.of Astronautics,Northwestern Polytechnical Univ.,Xi’an 710073,China;Coll.of Astronautics,Northwestern Polytechnical Univ.,Xi’an 710074,China;Coll.of Astronautics,Northwestern Polytechnical Univ.,Xi’an 710072,China;Shaanxi Inst.of Power Machinery,Xi’an 710025,China;Shaanxi Inst.of Power Machinery,Xi’an 710025,China

Published:2021-08-15

摘要/Abstract

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。

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

Abstract: 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.

Key words: Solid propellant rocket engine;Extendible exit cone nozzle+;Numerical simulation;Performance parameter

尤军峰,校金友,张铎,甘晓松,任全彬. 固体火箭发动机延伸喷管展开动力学分析[J]. 推进技术, 2008, 29(1): 37-42.