Simulation study on the influence of ignition cartridge location on ignition process in solid rocket motor
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摘要:
利用计算流体动力学（CFD）软件FLUENT的用户自定义函数（UDF）编程接口建立固体火箭发动机点火燃气加质模型、推进剂燃气加质模型，对不同点火药盒位置条件下的内外燃管型装药发动机点火瞬态过程进行模拟。计算结果表明：①点火药盒位置直接影响燃烧室内点火燃气的注入过程，进而影响燃烧室内不同区域的瞬态温度、压力变化过程；②中部点火条件下点火燃气同时向装药内通道两侧传播，推进剂内表面完全点燃所需时间最短；③头部点火、中部点火、尾部点火条件下燃烧室点火压强峰分别为10.741、9.862 MPa以及10.023 MPa，头部点火条件下的点火压强峰分别比中部点火、尾部点火高8.9%、7.16%；④尾部点火条件下部分点火燃气直接流出喷管外，点火燃气对推进剂传热减少，点火滞后期与火焰传播期增大，点火延迟高达12.75 ms。
Abstract:By using the user-defined function (UDF) programming interface of computational fluid dynamics (CFD) software FLUENT, the ignition gas and propellant gas dosing models of solid rocket motor were established. The transient process of motor ignition with different ignition cartridge locations was simulated. The results showed that: (1) The ignition location directly affected the injection process of ignition gas, thus affecting the transient temperature and pressure changes in different locations of the combustion chamber. (2) Under middle ignition condition, the ignition gas propagated to both sides of the inner passage of the propellant at the same time, resulting in the shorter time for the complete ignition of the inner surface on the propellant. (3) The ignition pressure peaks of combustion chamber under head ignition, middle ignition and tail ignition were 10.741, 9.862 MPa and 10.023 MPa, respectively. The ignition pressure peaks under head ignition were 8.9% and 7.16% higher than those under middle ignition and tail ignition, respectively. (4) Under the condition of tail ignition, the heat transfer of the ignition gas to the propellant decreased, the ignition lag period and the flame propagation period increased, and the ignition delay was as high as 12.75 ms.
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图 1 不同点火药盒位置发动机物理模型（单位：mm）
Figure 1. Physical model for different ignition cartridge locations （unit：mm）
图 6 实验与仿真的点火内弹道曲线对比
Figure 6. Ignition ballistic curves for test data and numerical results
图 7 不同点火药盒位置点火过程燃烧室温度变化
Figure 7. Chamber temperature changing at different times for different ignition cartridge locations
图 8 不同时刻3种点火药盒位置推进剂表面温度分布
Figure 8. Temperature on propellant surface at different times for three ignition cartridge locations
图 9 不同点火药盒位置点火过程中的燃烧室压力变化
Figure 9. Chamber pressure changing at different times for different ignition cartridge locations
图 10 不同时刻不同点火药盒位置发动机轴线压力分布
Figure 10. Pressure along axis in solid rocket motor at different times for different ignition cartridge locations
图 11 推进剂内表面已燃长度随时间变化
Figure 11. Burned length of the inner surface of the propellant varying with time
图 12 推进剂外表面已燃长度随时间变化
Figure 12. Burned length of the outer surface of the propellant varying with time
图 13 推进剂内表面火焰传播速度
Figure 13. Velocity of flame propagation on the inner surface of propellant
图 14 推进剂外表面火焰传播速度
Figure 14. Velocity of flame propagation on the outer surface of propellant
图 15 不同点火药盒位置发动机点火升压内弹道
Figure 15. Pressure history of the solid motor during ignition pressure buildup for different ignitor positions
图 16 点火药盒位置对点火过程内弹道特性参数影响
Figure 16. Effect of ignition cartridge locations on ballistic parameters in the ignition process
图 18 点火药盒位置对点火过程特性参数影响
Figure 18. Effect of ignition cartridge locations on ignition process parameters
参数 数值 推进剂密度$ \rho_{{\mathrm{p}}} $/（kg/m3） 1680 推进剂比定压热容cp,p/（J/（kg·K）） 1512 推进剂导热系数$ \lambda_{{\mathrm{p}}} $/（W/（m·K）） 0.24 推进剂着火温度$ T_{{\mathrm{b}}} $/K 700 推进剂燃速压强指数$ n $ 0.3 推进剂燃速系数$ a $/（m/（s·MPan）） 0.0047 点火药比定压热容$ c_{p, \mathrm{ig}} $/（J/（kg·K）） 1378 点火药燃气温度$ T_{{\mathrm{i g}}} $/K 2590 燃气温度$ T_{{\mathrm{g}}} $/K 2800 燃气比定压热容$ c_{p,{\mathrm{ g}}} $/（J/（kg·K）） 1680 燃气平均分子量$ M_{{\mathrm{g}}} $/（g/mol） 24.7 
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表 2 验证实验中的尺寸参数及物性参数[29]
Table 2. Dimensional parameters and physical property parameters in validation test[29]
参数 数值 推进剂尺寸外径$ D_{{\mathrm{p}}} $/mm 45 推进剂内径$ d_{{\mathrm{p}}} $/mm 8 推进剂长度$ L_{{\mathrm{p}}} $/mm 120 推进剂密度$ \rho_{{\mathrm{p}}} $/（kg/m3） 1640 推进剂比定压热容$ c_{p,{\mathrm{p}}} $/（J/（kg·K）） 1276 推进剂导热系数$ \lambda_{{\mathrm{p}}} $/（W/（m·K）） 0.32 推进剂着火温度$ T_{{\mathrm{b}}} $/K 700 燃气比定压热容$ c_{p,{\mathrm{g}}} $/（J/（kg·K）） 1516 燃气温度$ T_{{\mathrm{g}}} $/K 2860 推进剂燃速系数$ a $/（m/（s·MPan）） 0.0083 推进剂燃速压强指数$ n $ 0.26 点火药质量$ m_{{\mathrm{i g}}} $/g 4
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表 3 不同点火药盒位置点火过程内弹道特性参数
Table 3. Ballistic parameters in the ignition process for different ignition cartridge locations
点火药盒
位置点火
压力峰/
MPa内外通道
最大压差/
MPa最大
升压率/
（MPa/ms）喷管堵盖
打开时间/
ms头部点火 10.741 0.048 1.086 3.27 中部点火 9.862 0.242 1.082 4.21 尾部点火 10.023 0.070 1.022 4.80
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表 4 不同点火药盒位置点火过程性能参数
Table 4. Ignition process parameters for different ignition cartridge locations
ms 点火药盒位置 $ \Delta t_{1} $ $ \Delta t_{2} $ $ \Delta t_{3} $ $ \Delta t $ 头部点火 1.18 1.9 8.15 11.23 中部点火 1.34 3.66 7.01 12.01 尾部点火 2.33 4.02 6.4 12.75
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