偏置斜切喷管固体火箭发动机推力计算方法  

Thrust calculation method for solid rocket motorwith offset scarfed nozzle

作　　者：王立武 李春艳 李瑛 林志远 刘沛 WANG Liwu;LI Chunyan;LI Ying;LIN Zhiyuan;LIU Pei(The 41st Institute of the Fourth Academy of CASC,Science and Technology on Combustion,Internal Flow and Thermo-Structure Laboratory,Xi’an 710025,China;College of Astronauties,Nouthwestern Polytechnical University Science and Technology on Combustion,Internal Flow andThermo-Structure Laboratory,Xi’an 710072,China;The First Military Representative Officeof Rocket Military Equipment Department in Xi’an,Xi’an 710025,China)

机构地区：[1]中国航天科技集团有限公司四院四十一所固体火箭发动机燃烧、热结构与内流场国防科技重点实验室,西安710025 [2]西北工业大学燃烧、热结构与内流场重点实验室,西安710072 [3]火箭军装备部驻西安地区第一军事代表室,西安710025

出　　处：《固体火箭技术》2020年第4期407-413,共7页Journal of Solid Rocket Technology

摘　　要：为了解决采用偏置斜切喷管固体火箭发动机推力计算的难题,采用微元分割的方法,建立了适用于此类发动机的推力计算方法,可对发动机的推力及推力偏斜角进行计算。结果表明,针对实验发动机,该计算方法的压强和推力计算精度在±5%以内,可作为此类发动机推力预示的依据。揭示了此类发动机推力偏斜角产生的原因,由于喷管斜切部分对发动机的轴向推力和径向推力产生了不同影响,引起发动机的推力偏离喷管扩张段轴线方向,形成了推力偏斜角。针对此类发动机,喷管斜切部分产生的发动机轴向推力可能是负推力,在此类发动机设计过程中,应该科学地选择喷管偏置角和喷管斜切角,从而降低由于喷管偏置斜切而带来的发动机损失。In order to calculate the thrust of solid rocket motor(SRM)with offset scarfed nozzle structure,an especial calculation method based on the microelement segmentation was established to calculate thrust and thrust deviation angle of the SRM.The results show that the calculation accuracy of this method for chamber pressure and thrust of the experimental motor is not more than±5%,which can provide a significant reference for the SRM design.The results reveals the cause of thrust deviation angle,namely,the different influence of scarfed nozzle part on axial thrust and radial thrust of the SRM lead to the deviation of thrust direction from the axis direction of nozzle expansion section.For this SRM,the axial thrust that is from nozzle scarfed part may be less than zero.In the design process of the SRM,the offset angle and scarfed angle of nozzle should be selected scientifically to reduce the performance loss caused by offset scarfed nozzle.

关 键 词：偏置斜切喷管 固体火箭发动机 推力 计算方法 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]