摘要
为了获得偏置斜切喷管主要结构参数对发动机推力特性的影响规律,采用内弹道计算方法,通过对比不同喷管结构参数下发动机的推力特性,研究了喷管斜切角度和喷管扩张半角对发动机推力及推力偏斜角的影响规律。结果表明,随着发动机斜切角度的增大,发动机轴向推力略有增大,仅增大1%,发动机径向推力和推力偏斜角减小明显,分别减小28%和100%,且几乎呈线性关系;随着喷管扩张半角的增大,发动机轴向推力明显增大,增幅为14.8%,推力偏斜角显著减小,降幅为29.1%,而发动机径向推力略有增大,但仅增大1.2%。此外,喷管斜切部分产生的发动机轴向推力可能为负推力,即在斜切部分产生的轴向推力小于零,在发动机设计过程中应该重点关注,以期实现喷管结构的优化设计。
In order to understand the effects of the offset scarfed nozzle structure on the thrust in a solid rocket motor(SRM),a method of interior ballistic calculation was established.The effects of scarfed angle and expansion half angle on SRM thrust in studied by changing the structural parameters of a nozzle.The results show that with the increase of the scarfed angle of a nozzle,the increase of the axial thrust is very small(1%),the axial thrust and the thrust deviation angle decrease obviously,28%and 100%,respectively,and the relationship is almost linear.With the increase of the expansion half angle of a nozzle,the axial thrust increases obviously(14.8%),thrust deviation angle decrease obviously(29.1%),and the increase of the radial thrust is very small(1.2%).Moreover,the axial thrust produced by nozzle scarfed part may be negative,that is,the axial thrust that is from nozzle scarfed part may be less than zero,which should be taken into account during designing this kind of SRM,in order to realize the optimization design of the nozzle structure.
作者
惠博
闫宝任
李冰
刘英
王立武
XI Bo;YAN Baoren;LI Bing;LIU Ying;WANG Liwu(The Fourth Academy of China Aerospace Science and Technology Corporation,Xi’an 710025,China;The First Military Representative Office of Rocket Military Equipment Department in Xi’an,Xi’an 710000,China;Xi’an Aerospace XinYu Electromechanical Equipment Co.,Ltd.,Xi’an 710500,China)
出处
《固体火箭技术》
CAS
CSCD
北大核心
2021年第3期331-336,共6页
Journal of Solid Rocket Technology
