Investigation the control of the basic thermal environment of multistage launch vehicle at high altitude flight
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摘要:
采用数值模拟的方法，系统地研究了单喷管和四喷管多级液体运载火箭的基础热环境，并验证了箭底氮气喷射热防护方法的可行性。基于多组分Navier-Stokes方程、
k-ε 方程湍流模型、热辐射方程，运用AUSM格式对控制方程进行离散，建立了高空超声速飞行运载火箭的羽流模型。采用分块化网格构建法，计算了运载火箭在不同高度下的羽流流场和热流密度，并且将数值结果与飞行试验进行对比，验证了计算方法的可行性。研究表明在低海拔高度，箭底热流以对流热流为主，峰值出现在30 km处；在高海拔高度，箭底热流以辐射热流为主，峰值出现在110 km处；同时箭底氮气喷射装置能够有效地抑制燃气回流，起到降低箭底对流热流的效果，但是选择合适的喷口数量和喷射总压极为重要。Abstract:The basic thermal environment of one-engine and four-engine multi-stage liquid launch vehicles has been systematically investigated and the feasibility of the nitrogen injection thermal protection method at the rocket base has been verified by numerical simulation. Based on multi-component Navier-Stokes equation,
k -ε equation turbulence model and thermal radiation equation, the control equations were discretized using AUSM format to establish a plume model for high altitude supersonic flight launch vehicles. The plume flow field and heating rate of the launch vehicle at different altitudes were calculated using the blocked gird construction method, and the numerical results were compared with flight experiments to verify the feasibility of the calculation method. Study showed that at low altitudes, convection heating rate is dominant, with a peak at 30 km; at high altitudes, radiation heating rate is dominant, with a peak at 110 km; at the same time, the nitrogen injection device can effectively suppress gas backflow and reduce convection heating rate at the rocket base, but the selection of the right number of spouts and total injection pressure is extremely important. -
图 3 一级运载火箭在不同高度下的马赫数云图
Figure 3. Contour of Mach number of the C1 rocket at different altitudes
图 4 一级运载火箭在不同高度下的温度场云图
Figure 4. Contour of temperature of the C1 rocket at different altitudes
图 5 一级运载火箭在不同高度下的箭底对流热流和辐射热流云图
Figure 5. Contour of convection and radiation heating rate of the C1 rocket base at different altitudes
图 6 二级运载火箭在不同高度下的箭底对流热流和辐射热流云图
Figure 6. Contour of convection and radiation heating rate of the C2 rocket base at different altitudes
图 7 不同高度下的箭底最大对流热流与辐射热流对比图
Figure 7. Comparison of maximum convection and radiation heating rate of the rocket base at different altitudes
图 9 不同工况下的箭底对流热流云图
Figure 9. Contour of convection heating rate of the rocket base at different conditions
图 10 不同工况下的箭底附近压强云图
Figure 10. Contour of pressure near the rocket base at different conditions
图 11 不同工况下的箭底最大对流热流对比图
Figure 11. Comparison of maximum convection heating rate of the rocket base at different conditions
图 13 数值计算马赫数云图与试验对比
Figure 13. Comparison of Mach number between numerical calculation and experiment
表 1 自由流条件参数
Table 1. Free flow condition parameters
工况号 H/km Ma p/Pa T/K 1 5 0.6 54020 255.65 2 10 1.2 26436 223.15 3 20 2.1 5300 256.00 4 30 3.0 1172 226.65 5 40 4.0 259 251.05 6 60 6.2 20 245.45 7 75 6.71 2.3880 208 8 100 7.69 0.0320 195 9 110 7.89 0.0071 240 10 120 8.02 0.0052 232 
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表 2 氮气喷射工况设置
Table 2. Nitrogen injection condition setting
工况号 H/km T（N）/K p（N）/MPa 1 30 2 30 400 0.05 3 30 400 0.5 4 30 400 1
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