高原环境续航火箭喷管推力降低异常现象

张涪; 王鹏新; 阮文俊; 王浩; 朱晨光

doi:10.13224/j.cnki.jasp.2015.07.027

高原环境续航火箭喷管推力降低异常现象

doi: 10.13224/j.cnki.jasp.2015.07.027

1. 南京理工大学能源与动力工程学院, 南京 210094;
2. 中国人民解放军白城兵器试验中心, 吉林白城 137001;
3. 南京理工大学化工学院, 南京 210094

基金项目:

国家自然科学基金(51076066)

详细信息

作者简介:
张涪(1983-),男,河北邯郸人,博士生,主要从事高原环境续航火箭飞行稳定性方面的研究.

中图分类号: V231.3
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出版历程
- 收稿日期: 2014-05-11
- 刊出日期: 2015-07-28

Abnormal phenomenon of thrust reduction of range rocket nozzle under high altitude condition

1. School of Energy and Power Engineering, Nanjing University of Science and Technology, Nanjing 210094, China;
2. Baicheng Ordnance Test Center, the Chinese People's Liberation Army, Baicheng Jilin 137001, China;
3. School of Chemical Engineering, Nanjing University of Science and Technology, Nanjing 210094, China

摘要

摘要: 为了研究某种续航火箭喷管推力的异常现象,采用AUSM+(advection upstream splitting method)格式、SST(shear stress transport)湍流模型和LU-SGS(lower-upper symmetric Gauss-Seidel)隐式算法,求解二维轴对称RANS(Reynolds averaged Navier-Stokes)方程,对入口压力相同、环境压力不同的该喷管进行了数值模拟,得到了在环境压力为50.67~101.32kPa下其推力特性的差异,并分析了异常现象产生的原因.结果表明:随着环境压力的降低,外喷管出口边界的静推力为负值且绝对值呈现先增加后减小的变化规律.在环境压力为60.80~101.32kPa区间范围时,外喷管出口边界的动推力和总推力变化相对较小,当环境压力小于60.80kPa时,该出口边界的动推力和总推力急剧降低.
- 高原环境 /
- 续航火箭 /
- 潜入式喷管 /
- 推力降低 /
- 异常现象
Abstract: To research abnormal phenomenon of thrust reduction of a range rocket nozzle was chosen to study, nozzle with the same inlet pressure and different environment pressures were simulated numerically by applying the AUSM+ (advection upstream splitting method)scheme,SST(shear-stress transport) turbulence model and LU-SGS(lower-upper symmetric Gauss-Seidel)implicit algorithm were used to solve 2-D axial symmetry RANS(Reynolds-averaged Navier-Stokes) equations. The differences in thrust characteristics were obtained when the environment pressure varied from 50.67kPa to 101.32kPa, and the cause of these differences was analyzed. Results indicate that static thrust of the outer nozzle exit boundary rises toward the negative direction when the environment pressure gradually decreases, absolute value increases firstly and then decreases. Dynamic thrust and total thrust of the outer nozzle exit boundary slightly changes at the environment pressure ranging from 60.80kPa to 101.32kPa, but dynamic thrust and total thrust of the outer nozzle declines sharply when the environment pressure is less than 60.80kPa.
- high altitude condition /
- range rocket /
- submerged nozzle /
- thrust reduction /
- abnormal phenomenon

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参考文献(15)

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