发射过程中工质气体从侧向进入发射筒作用在导弹底部，导弹发动机喷管上将承受较大载荷，针对该问题建立了发射筒底部三维非稳态流场的数值模拟方法，并利用试验数据对该方法进行了校验。数值模拟结果表明，发射用工质气体近乎集中的作用到喷管特定区域是导致喷管载荷较大的主要原因。本文提出了一种能够改善发射筒底部流场结构、降低喷管受力的降载装置。进一步的数值模拟结果表明降载装置可以使喷管所受的最大总力矩下降26%，试验验证结果表明所提出的改进措施能够有效降低喷管所受载荷。
During launch process,the ejection gas enters the launch tube from the lateral inlet and then acting on the tall of the missile,which brings heavy load on the missile,which brings heavy load on the missile nozzle. In order to solve this problem, numerical simulation method of the three-dimensional unsteady flow field at the bottom of the launcher is established and verified by launching experiment. The numerical simulation results show that the main reason for the abnormal force on the nozzle is caused by excessive concentration of ejection gas on the specific region of nozzle surface. A device for controlling the fluid field of launcher and reducing the force load on the missile nozzle is designed. Further numerical simulation results show that the device can reduce the maximum total moment on the nozzle by 26%. The experiment results show that the new designed device can reduce the load of the nozzle and satisfy the requirements of nozzle servo control system.
2018,40(12): 146-149 收稿日期：2018-06-07
DOI：10.3404/j.issn.1672-7649.2018.12.030
分类号：V553
作者简介：汪太琨(1966-),女,研究员,研究方向为发动机设计
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