固体火箭发动机复合材料燃烧室外压稳定性研究  

External pressure stability of solid rocket motor chamber

作　　者：王健儒[1] 王莹 刘凯 敖麟 檀叶 张爱华 WANG Jianru;WANG Ying;LIU Kai;AO Lin;TAN Ye;ZHANG Aihua(Academy of Aerospace Solid Propulsion Technology,Xi'an 710025,China;Xi'an Institue of Aerospace Solid Propulsion Technology,National Key Laboratory of Solid Rocket Propulsion,Xi'an 710025,China)

机构地区：[1]航天动力技术研究院,西安710025 [2]西安航天动力技术研究所,固体推进全国重点实验室,西安710025

出　　处：《固体火箭技术》2023年第6期923-929,共7页Journal of Solid Rocket Technology

摘　　要：为了研究固体火箭发动机的外压承载能力,采用非线性有限元分析方法,对未填充药柱复合材料壳体、带药燃烧室的外压承载能力进行了仿真分析,并采用试验方法对仿真结果进行校验。研究结果表明,带药燃烧室的外压承载能力明显高于未填充药柱的复合材料壳体,药柱对燃烧室的承载能力有增强效果。此外,燃烧室内部充压能够有效提高其外压承载能力,且内部压强与燃烧室外压承载能力几乎呈线性关系。同时,还发现对于环槽加中孔药型,当药柱模量较低时,筒段为外压承载的薄弱部位,药柱模量增加有利于提高燃烧室失稳外压临界值;但是当药柱模量增加至一定程度时,封头由于环槽部位药柱肉厚较薄而转变为新的薄弱部位,药柱模量增加燃烧室失稳外压临界值并不增加。In order to study the external pressure bearing capacity of solid rocket motor,the deformation of chamber with propel-lant grain and composite case under external pressure was simulated by means of nonlinear finite element analysis method,and the simulation results were verified with experimental methods.The results show that the external pressure bearing capacity of the cham-ber with propellant is significantly higher than that of the case,and the grain has an enhanced effect on the bearing capacity of the chamber.In addition,the internal pressure of the chamber can effectively improve its external pressure bearing capacity,and the ex-ternal pressure bearing capacity of the chamber is almost linearly related to the internal pressure.Meanwhile,it is found that the cyl-inder section is the weakest part under external pressure for annular groove grain configuration with low modulus,and the increase in grain modulus can improve stability of chamber under external pressure.However,when the modulus increases to a certain value,the dome head becomes the new weak part due to the thinner web thickness near the annular groove,and the increase in grain modulus cannot improve the stability of chamber under external pressure any longer.

关 键 词：固体火箭发动机 燃烧室 复合材料壳体 外压稳定性 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]