摘要
为研究某舰载固体火箭发动机在巡航状态下药柱的损伤情况,评估其在摇摆载荷作用下的力学结构响应和安全裕度。首先,开展了所用HTPB推进剂的循环载荷拉伸试验,拟合出载荷-寿命(S-N)曲线;之后,建立了全尺寸固体火箭发动机模型,通过有限元分析方法计算得到发动机药柱的应力和应变,得到其最大Mises应力为0.03 MPa,最大主应变为1.746%;最后,结合S-N曲线得到舰艇巡航一定时间后药柱能承受的循环载荷上限值,评估不同巡航时间下发动机药柱的安全系数。结果表明,固体火箭发动机随舰艇巡航一段时间后,药柱危险点位于前人工脱粘层凸环界面,不会直接使发动机药柱受到破坏,但会影响发动机的安全裕度。
In order to study the damage of grain of a shipborne solid rocket motor(SRM)under cruising state,the mechanical structure response and safety margin under rocking load were evaluated.Firstly,the cyclic load tensile test of the HTPB propellant was carried out to fit the stress⁃cycle index(S⁃N)curves;Secondly,the full⁃scale SRM model was established,and the stress⁃strain contours of the SRM grain were calculated by finite element analysis method.The maximum Mises stress is 0.03 MPa and the maxi⁃mum principal strain is 1.746%.And finaly,combined with the S⁃N curves,the upper limit of cyclic load that the grain can bear after cruising for a certain time was obtained,and the safety factor of the SRM grain under different cruising time was evaluated.The results show that after the SRM cruisings for a period of time,the dangerous point of the shipborne SRM grain is located at the con⁃vex ring interface of the front artificial debonding layer,which can not directly damage the grain of the SRM,but will affect the safety margin of the SRM.
作者
孙新智
何景轩
沙宝林
郜捷
SUN Xinzhi;HE Jingxuan;SHA Baolin;Gao Jie(The Institute of Xi'an Aerospace Solid Propulsion Technology,Xi'an710025,China)
出处
《固体火箭技术》
CAS
CSCD
北大核心
2023年第4期551-556,共6页
Journal of Solid Rocket Technology
