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发表时间：2016-01-01
发表刊物：推进技术
所属单位：运载工程与力学学部
期号：3
页面范围：436-442
ISSN号：1001-4055
摘要：For thrust vector control by injection bled from combustor,the flowfield of three schemes of in-jection,injected into nozzle,to outside of missile without and with wings,was calculated and analyzed by nu-merical simulation method. Numerical simulation results show that the lateral force change with different jet posi-tion 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.
备注：新增回溯数据