Simulation of thrust control by fluidic injection and pintle in a solid rocket motor

被引：30

作者：

Yan, Dongfeng ^{[1
]}

Wei, Zhijun ^{[1
]}

Xie, Kan ^{[1
]}

Wang, Ningfei ^{[1
]}

机构：

[1] Beijing Inst Technol, Jet Prop Lab, Sch Aerosp Engn, 5 South Zhongguancun St, Beijing 100081, Peoples R China

来源：

AEROSPACE SCIENCE AND TECHNOLOGY | 2020年 / 99卷

关键词：

Pintle motor; Ablation protection; Variable thrust; Solid rocket motor; Fluidic nozzle throat; PERFORMANCE;

D O I：

10.1016/j.ast.2020.105711

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Thrust control enables solid rocket motors to be more manoeuverable and controllable. To improve the thrust control and anti-ablative performance of solid rocket motors, a new type of motor controlled by secondary flow and a pintle is proposed: numerical simulation of two typical pintle thrusters is presented. The influence of different pintle positions, injection angle, and flow ratios on the effective throat area ratio, outlet pressure, and wall temperature of the pintle were studied. The results showed that the new type of motor can reduce the wall temperature of the pintle. Increasing the secondary flow ratio and injecting the secondary flow in reverse can increase control performance. When the total flow rate is constant, the injection of a secondary flow can reduce the outlet pressure. (C) 2020 Elsevier Masson SAS. All rights reserved.

引用

页数：10

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