发动机引流推力矢量方案数值研究

推进技术 ›› 2016, Vol. 37 ›› Issue (3): 436-442.

发动机引流推力矢量方案数值研究

孙得川,由旭

大连理工大学航空航天学院，工业装备结构分析国家重点实验室，辽宁大连 116024,大连理工大学航空航天学院，工业装备结构分析国家重点实验室，辽宁大连 116024

发布日期:2021-08-15
作者简介:孙得川，男，博士，教授，研究领域为火箭发动机，计算流体动力学。
基金资助:
航空基金(20120163001)。

Numerical Research on Thrust Vector Control Scheme by Injection Bled from Motor

School of Aeronautics and Astronautics，Dalian University of Technology，State Key Laboratory of Structural Analysis for Industrial Equipment，Dalian 116024，China and School of Aeronautics and Astronautics，Dalian University of Technology，State Key Laboratory of Structural Analysis for Industrial Equipment，Dalian 116024，China

Published:2021-08-15

摘要/Abstract

摘要： 针对从燃烧室引流喷射的推力矢量控制方案，采用数值模拟的方法进行流场计算与分析，比较了引流向喷管内喷射、向无弹翼的弹体外侧喷射和向有弹翼的弹体外侧喷射三种方案。数值模拟结果表明:向喷管内引流的侧向力与喷流位置和喷射角度相关，最大侧向力与轴向推力的比值与引流管喉部面积占总喉部面积的比值大致相等；向弹体外引流时，喷口附近的弹翼对流场有很大的影响，若没有弹翼，则侧向力放大因子小于1，不宜采用；弹翼对喷流侧向力起显著的增强作用，放大因子可达1.5或更高。

关键词: 固体火箭发动机；喷流；推力矢量；喷管；导弹；数值模拟

Abstract: For thrust vector control by injection bled from combustor，the flowfield of three schemes of injection，injected into nozzle，to outside of missile without and with wings，was calculated and analyzed by numerical simulation method. Numerical simulation results show that the lateral force change with different jet position and injection angle when gas injected into nozzle. The maximum ratio of lateral force to axial thrust is nearly equal to the ratio of the tube throat area to the total throat area. When gas injected outside of the missile body，the wings nearby the lateral jet have great effect on the flowfield. If without wings，the lateral force amplification factor is less than 1，so that this kind of scheme should not be used. If wings exist，the amplification factor will be increased significantly and approach to1.5 or higher.

Key words: Solid rocket motor；Injection；Thrust vector；Nozzle；Missile；Numerical simulation

孙得川,由旭. 发动机引流推力矢量方案数值研究[J]. 推进技术, 2016, 37(3): 436-442.

SUN De-chuan,YOU Xu. Numerical Research on Thrust Vector Control Scheme by Injection Bled from Motor[J]. Journal of Propulsion Technology, 2016, 37(3): 436-442.

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