WALTRUP P J , WHITE M E , ZARLINGO F , et al . History of U.S. Navy ramjet, scramjet, and mixed-cycle propulsion development [J ] . Journal of Propulsion and Power , 2015 , 18 ( 1 ): 14 - 27 . DOI: 10.2514/2.5928 http://doi.org/10.2514/2.5928 https://arc.aiaa.org/doi/10.2514/2.5928 https://arc.aiaa.org/doi/10.2514/2.5928

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STOCKENSTROM A . Numerical model for analysis and specification of a ramjet propelled artillery projectile [C ] // Proceedings of the 19th International Symposium on Ballistics.Interlaken, Switzerland:IBC , 2001 : 537 - 544 .

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张宁 , 史金光 , 马晔璇 . 冲压增程制导炮弹气动特性研究 [J ] . 兵工学报 , 2020 , 41 ( 3 ): 460 - 470 . DOI: 10.3969/j.issn.1000-1093.2020.03.006 http://doi.org/10.3969/j.issn.1000-1093.2020.03.006 为研究冲压增程制导炮弹在不同弹道阶段的气动特性，依据其工作原理与飞行特点，设计冲压助推、爬升飞行、滑翔控制状态所对应的3种气动外形。运用拼接网格技术与雷诺转捩模型，对冲压增程制导炮弹的三维流场与气动特性进行模拟和数值计算。结果表明：3种气动外形与相同外形参数（除舵翼与头部母线外）但不采用冲压结构形式的鸭式布局制导炮弹（参考弹）相比，升阻力系数规律一致；冲压助推、滑翔控制、爬升飞行外形在相同条件下对应的阻力系数依次递减，分别较参考弹阻力系数增大约50.5%、42.9%、33%；滑翔控制外形因鸭舵展开，相同条件下升力系数较其他两种外形大，又因进气道限制了鸭舵面积，相同条件下升力系数较参考弹小（约小11.9%）；弹体摆动减小了冲压发动机进气道的流量系数和总压恢复系数，对其总体性能产生了不利影响。

ZHANG N , SHI J G , MA Y X . Research on aerodynamic characteristics of solid fuel ramjet guided projectile [J ] . Acta Armamentarii , 2020 , 41 ( 3 ): 460 - 470 . (in Chinese) DOI: 10.3969/j.issn.1000-1093.2020.03.006 http://doi.org/10.3969/j.issn.1000-1093.2020.03.006 In order to study the aerodynamic characteristics of the solid fuel ramjet guided projectile in different ballistic stages, three aerodynamic configurations corresponding to the states of ramjet assisting, climbing flight and gliding control are designed according to the working principle and flight characteristics of projectile. The Renault transition model is used to simulate and numerically calculate the three-dimensional flow field and aerodynamic characteristics of solid fuel ramjet guided projectile. The results show that comparison of the three aerodynamic configurations with the same shape parameters（except for canard and head bus）do not adopt the ramjet of the duck-type layout guided projectile (reference projectile), the lift resistance coefficient is the same; the drag coefficients of punching boost, gliding control, and climbing flight shape under the same conditions are increased by 50.5%,42.9% and 33%, respectively, compared to the reference drag coefficient; the gliding control shape is unfolded due to the duck rudder. The lift coefficient is larger than the other two shapes under the same conditions, and the duck rudder area is limited by the air inlet. The lift coefficient is smaller than that of the reference bomb under the same conditions; and the flow path structure inside the shape has a slight influence on the lift.Key

FOSS C F . Ammo working on ramjet-powered 155mm artillery round [J ] . Jane’s Defence Weekly , 2017 , 54 ( 22 ): 6 .

MCDONAL B , RICE J . Solid fuel ramjet fuel optimization for maximum thrust to drag ratio and impulse density subject to geometric restraints on missile outer mold line [J ] . Aerospace Science and Technology , 2018 , 75 ( 4 ): 47 - 57 . DOI: 10.1016/j.ast.2018.01.008 http://doi.org/10.1016/j.ast.2018.01.008 https://linkinghub.elsevier.com/retrieve/pii/S1270963817323556 https://linkinghub.elsevier.com/retrieve/pii/S1270963817323556

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HUANG J , YAO W X . Multi-objective design optimization of blunt body with spike and aero disk in hypersonic flow [J ] . Aerospace Science and Technology , 2019 , 93 : 105122 . DOI: 10.1016/j.ast.2019.04.030 http://doi.org/10.1016/j.ast.2019.04.030 https://linkinghub.elsevier.com/retrieve/pii/S1270963818322739 https://linkinghub.elsevier.com/retrieve/pii/S1270963818322739

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张珺 , 李立州 , 原梅妮 . 径向基函数参数化翼型的气动力降阶模型优化 [J ] . 应用数学和力学 , 2019 , 40 ( 3 ): 250 - 258 .

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FEI C W , LI H , LIU H T , et al . Enhanced network learning model with intelligent operator for the motion reliability evaluation of flexible mechanism [J ] . Aerospace Science and Technology , 2020 , 107 : 106342 . DOI: 10.1016/j.ast.2020.106342 http://doi.org/10.1016/j.ast.2020.106342 https://linkinghub.elsevier.com/retrieve/pii/S1270963820310245 https://linkinghub.elsevier.com/retrieve/pii/S1270963820310245

YUN W , LU Z , HE P , et al . Adaptive subdomain sampling and its adaptive kriging-based method for reliability and reliability sensitivity analyses [J ] . Structural and Multidisciplinary Optimization , 2020 , 61 : 1107 - 1121 . DOI: 10.1007/s00158-019-02412-6 http://doi.org/10.1007/s00158-019-02412-6

FEI C W , LI H , LU C , et al . Vectorial surrogate modeling method for multi-objective reliability design [J ] . Applied Mathematical Modelling , 2022 , 109 : 1 - 20 . DOI: 10.1016/j.apm.2022.03.033 http://doi.org/10.1016/j.apm.2022.03.033 https://linkinghub.elsevier.com/retrieve/pii/S0307904X2200155X https://linkinghub.elsevier.com/retrieve/pii/S0307904X2200155X

CHENZ Q , ZHAO Y H , YANG R . Parametric reduced-order modeling of unsteady aerodynamics for hypersonic vehicles [J ] . Aerospace Science and Technology , 2019 , 87 : 1 - 14 . DOI: 10.1016/j.ast.2019.01.035 http://doi.org/10.1016/j.ast.2019.01.035 https://linkinghub.elsevier.com/retrieve/pii/S1270963818308435 https://linkinghub.elsevier.com/retrieve/pii/S1270963818308435

陈雄 , 朱国强 , 郑健 . 聚甲基丙烯酸甲酯在固体燃料冲压发动机中的燃面退移速率影响因素研究 [J ] . 兵工学报 , 2015 , 36 ( 9 ): 1632 - 1639 . DOI: 10.3969/j.issn.1000-1093.2015.09.005 http://doi.org/10.3969/j.issn.1000-1093.2015.09.005 采用数值计算与实验研究相结合的方法，对聚甲基丙烯酸甲脂（PMMA）在固体燃料冲压发动机中的燃速影响因素开展了研究。重点分析了来流空气质量通量和固体燃料装药内径对PMMA燃料平均燃速和局部燃速的影响。研究表明：固体燃料表面的温度、热流密度和局部燃面退移速率沿轴线方向均呈现先逐渐增大后逐渐减小的趋势，极值出现在回流区末端的再附着点附近；固体燃料表面的局部燃面退移速率随装药内径增大而减小，但随空气质量通量的增大而增大；燃料平均燃速与来流空气质量通量呈幂函数递增关系，与固体燃料装药内径呈幂函数递减关系；数值计算和实验得到的影响变化规律吻合较好，但计算值比实验值稍微偏高，最大误差不超过10%. 研究结果对固体燃料冲压发动机燃烧室的优化设计具有重要的参考价值。

CHEN X , ZHU G Q , ZHENG J . Research on influence of selected factors on fuel surface regression rate of PMMA in solid fuel ramjet [J ] . Acta Armamentarii , 2015 , 36 ( 9 ): 1632 - 1639 . (in Chinese) DOI: 10.3969/j.issn.1000-1093.2015.09.005 http://doi.org/10.3969/j.issn.1000-1093.2015.09.005 Numerical simulation and direct connected test methods are used to study the influences of selected factors on the fuel surface regression rate of polymethylmethacrylate (PMMA) in a solid fuel ramjet. The influences of air mass flux and fuel internal diameter on the solid fuel average regression rate and local regression rate are studied. The results show that the temperature, heat flux and local regression rate of the solid fuel surface firstly increase and then decrease gradually along the axial direction, and reach the maximum values at the reattachment point in the end of the recirculation zone. The local regression rate of the fuel surface increases with the inner radius of fuel, but decreases with the mass flux of the air. The average regression rate of the fuel shows an increasing power function relation with air mass flux and a decreasing power function relation with fuel internal diameter. The numerical simulation results are coincident with the experimental results, and are slightly larger than experimental results. The maximum error is less than 10%.

巩伦昆 , 陈雄 , 周长省 , 等 . 结构尺寸对固体燃料冲压发动机燃速影响的仿真研究 [J ] . 兵工学报 , 2016 , 37 ( 5 ): 798 - 807 . DOI: 10.3969/j.issn.1000-1093.2016.05.005 http://doi.org/10.3969/j.issn.1000-1093.2016.05.005 为研究结构尺寸对固体燃料冲压发动机燃速的影响规律，采用3阶单调迎风（MUSCL）重构方法，AUSMPW+通量分裂格式，k-w SST湍流模型，7组分3反应有限速率化学反应模型以及2阶矩湍流燃烧模型，编制了二维轴对称湍流燃烧仿真程序，研究入口直径、药柱直径、喷喉直径以及相似结构尺寸对燃速的影响规律。仿真结果表明：入口直径以及药柱直径影响较大，相似结构尺寸的影响相对较小，喷喉直径几乎没有影响；固体燃料冲压发动机结构尺寸影响燃速的主要机理是湍流黏性的变化以及火焰面位置的变化；突扩比对燃速起着关键的作用，燃速与突扩比近似呈线性关系。

GONG L K , CHEN X , ZHOU C S , et al . Numerical investigation on effect of solid fuel ramjet geometry on solid fuel regression rate [J ] . Acta Armamentarii , 2016 , 37 ( 5 ): 798 - 807 . (in Chinese)

雷娟棉 , 谭朝明 . 基于Transition SST模型的高雷诺数圆柱绕流数值研究 [J ] . 北京航空航天大学学报 , 2017 , 43 ( 2 ): 207 - 217 .

LEI J M , TAN C M . Numerical simulation for flow around circular cylinder at high Reynolds number based on Transition SST model [J ] . Journal of Beijing University of Aeronautics and Astronautics , 2017 , 43 ( 2 ): 207 - 217 . (in Chinese)

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彭灯辉 , 王丹丹 , 杨涛 , 等 . 固体燃料冲压发动机燃烧效率建模与数值分析 [J ] . 推进技术 , 2014 , 35 ( 2 ): 251 - 256 .

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张宁 , 史金光 , 王中原 , 等 . 带有钝体的弹用固体燃料冲压发动机工作性能 [J ] . 兵工学报 , 2022 , 43 ( 7 ): 1519 - 1526 . DOI: 10.12382/bgxb.2021.0428 http://doi.org/10.12382/bgxb.2021.0428 为发展一种弹用高性能冲压发动机，提出了在补燃室带有钝体的发动机设计方案，并数值计算对比分析了补燃室有无钝体方案下的内流场、燃烧效率、推力、比冲与总压损失。结果表明：钝体后部孔隙外侧有两个漩涡，孔隙内的高速气流与下部漩涡在一定程度维持了尾迹的稳定性，能够保证冲压发动机工作的平稳性；与参考固体燃料冲压发动机（不带钝体结构方案）相比，在补燃室中增加钝体能提高补燃室下游燃料与空气的掺混效果与温度，当进气质量流率为0.3 kg/s时，可使发动机推力和比冲提高约16.21%、燃烧效率提高约20.50%，但此增益效果会随着空燃比的增大而减小；当燃烧效率相同时，在补燃室中增设钝体，可以有效地缩减冲压发动机长度，为其他部件提供安装空间。

ZHANG N , SHI J G , WANG Z Y , et al . Performance of solid fuel ramjet with central bluff body for projectile [J ] . Acta Armamentarii , 2022 , 43 ( 7 ): 1519 - 1526 . (in Chinese) DOI: 10.12382/bgxb.2021.0428 http://doi.org/10.12382/bgxb.2021.0428 To develop a high-performance ramjet for projectiles, a scheme of using bluff bodies in the combustion chamber of the solid fuel ramjet is proposed. The turbulent combustion model is established based on equations for Reynolds transition and eddy dissipation, and the internal flow field, combustion efficiency, thrust, specific impulse and total pressure loss of the combustion chamber with or without the bluff body are compared and analyzed by numerical calculation. The findings show that there are two vortices outside the pore behind the central bluff body. The high-speed airflow in the pore and small-scale vortices below has maintained some wake stability, which can ensure the smooth operation of the ramjet. Compared with the reference solid fuel ramjet (without bluff body structure), adding a bluff body in the afterburning chamber can improve the mixing effect and temperature of fuel and air at the downstream of this chamber, which can increase the combustion efficiency. When the intake air mass flow rate was 0.3 kg/s, the ramjet thrust and specific impulse was increased by about 16.21%, and the combustion efficiency improved by about 20.50%, but the enhancement effects would decrease with the increase of air-fuel ratio. Under the same combustion efficiency, adding a bluff body in the combustion chamber can effectively reduce the length of the ramjet and thus leaving installation space for other parts.

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