Force on the pintle of pintle variable thrust solid rocket motor
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摘要:
为研究不同因素对针栓式变推力固体火箭发动机内流场流动特性、发动机性能参数及针栓所受载荷的影响，探究其控制性能，采用数值仿真的方法，对不同针栓型面及针栓尾部凹槽设计下的喷管内流场进行计算研究。结果表明：针栓式变推力固体火箭发动机的推力调节范围很大，针栓受力变化也大；针栓型面的改变对针栓载荷无显著影响，最大载荷下降28%；针栓尾部凹槽的设计可以在较大程度上平衡针栓载荷，最大载荷下降56%；针栓阀体导流槽的设计对于针栓所受载荷的降低有显著作用，最大载荷下降91%，大大增强了针栓式变推力固体火箭发动机的控制性能。
Abstract:The influences of different factors on the flow characteristics of the internal flow field, the motor performance parameters and the force on the pintle were studied, and the control performance of the pintle motor was explored. Based on the method of numerical simulation, the flow field in nozzle under different pintle profiles and pintle tail groove designs was calculated and studied. The results showed that the thrust adjustment range of pintle variable thrust solid rocket motor was large, and the force variation of pintle was also large. The change of pintle profile had no significant effect on pintle load, and the maximum load decreased 28%. The design of the tail groove of the pintle can balance the pintle load to a large extent, and the maximum load was reduced by 56%. The design of the guide groove of the valve body of the pintle had a significant effect on reducing the force on the pintle, and the maximum load decreased 91%, which greatly enhanced the control performance of the pintle variable thrust solid rocket motor.
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Key words:
- pintle /
- solid rocket motor /
- load analysis /
- pintle profile /
- groove balance /
- drainage design
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图 1 针栓式变推力固体火箭发动机结构示意图
Figure 1. Schematic of structure of pintle variable thrust solid rocket motor
图 3 10种针栓型面At.eq随针栓行程的变化曲线
Figure 3. Variations of At.eq with pintle position of 10 pintle profiles
图 10 不同型面针栓介入下的喷管内流场马赫数分布图
Figure 10. Mach number contours of inner flow field with different profile pintles
图 11 不同型面针栓作用下出口马赫数和径向速度分布
Figure 11. Outlet Mach number and radial velocity distribution with different profile pintles
图 14 位置1和位置4不同凹槽深度下的
${F_{\text{p}}}$ Figure 14.
${F_{\text{p}}}$ with different groove height at position 1 and 4表 1 针栓式变推力固体火箭发动机几何参数
Table 1. Geometric parameters of pintle variable thrust solid rocket motor
mm 参数 数值 燃烧室半径Rc 45 喉部半径Rt 17.5 喷管出口半径Re 53.24 收敛段长度Lc 32 扩张段长度Le 82 喉部平直段长度Lt 5 发动机总长L 197 针栓半径Rp 17 针栓头部高度h 20 针栓头部半径R0 1 
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表 2 燃气参数
Table 2. Parameters of gas
γ Tc/K cp/（J/（kg·K）） M Rg/（J/（kg·K）） 1.25 1998.5 1 957 21 395.9
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表 3 针栓4个位置的数据
Table 3. Data for 4 pintle positions
参数 位置1 位置2 位置3 位置4 s/mm 0 11.80 15.30 20.50 At,eq/mm2 853.96 424.82 297.47 82.74 $\dot m$/（kg/s） 6.24 3.17 2.20 0.64 Ft/N 16314 7833 5967 1633 Is/（N·s/kg） 2614 2471 2712 2552
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表 4 不同型面针栓作用的发动机性能计算结果比较
Table 4. Motor performance with different profile pintles
针栓型面 Ft/N Is/（N·s/kg） Fp/N p0,e/p0,c A 1633.62 2678.70 481.58 0.79 B 770.01 2036.40 −13.92 0.83 C 1120.48 2618.10 254.37 0.80 D 1640.46 2702.33 459.86 0.83 E 1643.30 2666.01 457.63 0.75 F 1660.66 2688.26 467.68 0.80 G 1650.94 2698.42 465.06 0.80 H 1580.55 2726.96 447.72 0.79 I 1199.16 2651.02 301.92 0.76 J 1671.68 2673.12 468.97 0.77
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表 5 针栓所受载荷总结
Table 5. Pintle load summary
针栓型面 位置1 位置4 ${F_{\text{p}}}$/N ${F_{\text{p} } }/{F_{ {\text{t,max} } } }$ ${F_{\text{p}}}$/N $\left| { {F_{\text{p} } }/{F_{ {\text{t,max} } } }} \right|$ 初始型面 5071 1 481 0.09 ${h_{\text{c}}}$= 2 mm 3168 0.62 −1249 0.25 ${h_{\text{c}}}$= 3 mm 2403 0.47 −2023 0.40 ${h_{\text{c}}}$= 4 mm 1691 0.33 −2744 0.54 导流槽设计型面 476 0.09 −77 0.02
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