火箭推进

使用无旋特征线法和拟抛物线公式对某地面启动喷管进行了设计,考虑了4种常用的钟型喷管型面,即最大推力喷管、最优抛物线喷管、截短理想喷管、压缩截短理想喷管。通过使用自编高效欧拉方程耦合附面层修正喷管流场求解器求解流场,得到喷管在绝热条件下的真空比冲、出口壁面压力等关键信息,然后使用FLUENT软件计算喷管的流动分离状态,进而比较了这4类常用的钟型喷管的性能和低空使用边界。结果表明,4类喷管在该设计条件下性能差距很小,但是抛物线喷管和压缩截短理想喷管均可通过调整型面来提高喷管出口壁面压力从而扩大喷管的可用面积比进而提高比冲。

A ground starting nozzle was designed by using the non-rotation characteristic line method and quasi-parabolic formula. Four common bell-shaped nozzles were considered, namely, maximum thrust nozzle, optimal parabolic nozzle, truncated ideal nozzle and compressed truncated ideal nozzle. By using a self-designed and efficient Euler equation coupled boundary layer modified nozzle flow field solver to solve the flow field, the key information of nozzle under the adiabatic condition such as vacuum specific impulse and outlet wall pressure were obtained. Then, the flow separation state of nozzle was calculated by FLUENT software, and the performance and low altitude operating boundary of these four commonly used bell nozzles were compared. The results show that the performance difference of the four types of nozzles is very small under the design condition, but both parabolic nozzle and compressed truncated ideal nozzle can improve the outlet wall pressure by adjusting the shape surface, thereby enlarging the available area ratio of nozzle and improving the specific impulse.

引言
1 常用钟型喷管型面设计
2 喷管性能和流动分离计算方法
3 计算结果
4 结论

图1 最大推力喷管设计示意图<br/>Fig.1 Schematic diagram of TOC nozzle design

图1 最大推力喷管设计示意图
Fig.1 Schematic diagram of TOC nozzle design

图2 抛物线喷管设计示意图<br/>Fig.2 Schematic diagram of parabola nozzle design

图2 抛物线喷管设计示意图
Fig.2 Schematic diagram of parabola nozzle design

图3 理想喷管设计示意图<br/>Fig.3 Schematic diagram of ideal nozzle design

图3 理想喷管设计示意图
Fig.3 Schematic diagram of ideal nozzle design

图4 CTIC喷管设计示意图<br/>Fig.4 Schematic diagram of CTIC nozzle design

图4 CTIC喷管设计示意图
Fig.4 Schematic diagram of CTIC nozzle design

图5 计算域及边界条件<br/>Fig.5 Computational domain and boundary conditions

图5 计算域及边界条件
Fig.5 Computational domain and boundary conditions

图6 计算网格
Fig.6 Computational grid

图7 SSME流动分离计算马赫数云图<br/>Fig.7 Mach number cloud graph calculated by SSME flow separation

图7 SSME流动分离计算马赫数云图
Fig.7 Mach number cloud graph calculated by SSME flow separation

图8 CFD网格无关性验证<br/>Fig.8 CFD grid independence verification

图8 CFD网格无关性验证
Fig.8 CFD grid independence verification

图9 TOP喷管和CTIC喷管的真空比冲优化计算<br/>Fig.9 Optimization calculation of vacuum pressure for top nozzle and CTIC nozzle

图9 TOP喷管和CTIC喷管的真空比冲优化计算
Fig.9 Optimization calculation of vacuum pressure for top nozzle and CTIC nozzle

表1 4类喷管性能<br/>Tab.1 Performance of the four types of nozzle

表1 4类喷管性能
Tab.1 Performance of the four types of nozzle

图10 TOP喷管和CTIC喷管的壁面出口压力优化计算<br/>Fig.10 Optimization calculation of wall outlet pressure for top nozzle and CTIC nozzle

图10 TOP喷管和CTIC喷管的壁面出口压力优化计算
Fig.10 Optimization calculation of wall outlet pressure for top nozzle and CTIC nozzle

表2 4类喷管出口壁面压力<br/>Tab.2 Wall outlet pressure of the four types of nozzle

表2 4类喷管出口壁面压力
Tab.2 Wall outlet pressure of the four types of nozzle

表3 面积比为59的喷管出口壁面压力与真空比冲<br/>Tab.3 Wall outlet pressure and vacuum specific impulse of nozzle when area ratio is 59

表3 面积比为59的喷管出口壁面压力与真空比冲
Tab.3 Wall outlet pressure and vacuum specific impulse of nozzle when area ratio is 59

图11 面积比为49,35°入口角、3°出口角抛物线喷管马赫数云图<br/>Fig.11 Mach number cloud diagram of parabola nozzle with 49-area ratio, 35° entrance angle, 3° exit angle

图11 面积比为49,35°入口角、3°出口角抛物线喷管马赫数云图
Fig.11 Mach number cloud diagram of parabola nozzle with 49-area ratio, 35° entrance angle, 3° exit angle

图12 各类喷管流动分离仿真图像<br/>Fig.12 Simulation image of flow separation for various nozzles

图12 各类喷管流动分离仿真图像
Fig.12 Simulation image of flow separation for various nozzles

[1] 杨立军,富庆飞.液体火箭发动机推力室设计[M].北京:北京航空航天大学出版社,2013.
[2] ÖSTLUND J,MUHAMMAD K B.Supersonic flow separation with application to rocket engine nozzles[J].Applied Mechanics Reviews,2005,58(3):143-177.
[3] 叶正寅,吕广亮.火箭发动机喷管非定常侧向力和流固耦合研究进展[J].航空工程进展,2015,6(1):1-12.
[4] FREY M,HAGEMANN G,FREY M.Status of flow separation prediction in rocket nozzles[R].AIAA-2004-4162.
[5] MARTELLI E,NASUTI F,ONOFRI M.Numerical calculation of FSS/RSS transition in highly overexpanded rocket nozzle flows[J].Shock Waves,2010,20(2):139-146.
[6] RAO G R V.Exhaust nozzle contour for optimum thrust[J].Jet Propulsion,1985,28(6):377-382.
[7] RAO G R V.Approximation of optimum thrust nozzle contour[Z].1960.
[8] AHLBERG J H,HAMILTON S,MIGDAL D,et al.Truncated perfect nozzles in optimum nozzle design[J].ARS Journal,1961,31:614-620.
[9] HOFFMAN J.Design of compressed truncated perfect nozzles[EB/OL].https://www.semanticscholar.org/paper/Design-of-compressed-truncated-perfect-nozzles-Hoffman/782cd76e564677bcb46b6e8c6bb944b69a1f8c7d,1985.
[10] CHAN J,FREEMAN J A.Thrust chamber performance using Navier-Stokes solution[EB/OL].https://www.semanticscholar.org/paper/Thrust-chamber-performance-using-Navier-
[11] YANG V.Liquid rocket thrust chambers:Aspects of modeling,analysis,and design[M].Reston,Virginia:American Institute of Aeronautics and Astronautics,2004.
[12] LEE C,CHOI K,KIM C,et al.Computational investigations of side-loads in a thrust-optimized parabolic nozzle during high-altitude testing[C]//AIAA Scitech 2020 Forum.Reston,Virginia:AIAA,2020.
[13] TERHARDT M,HAGEMANN G,FREY M.Flow separation and side-load behavior of truncated ideal rocket nozzles[EB/OL].https://www.semanticscholar.org/paper/Flow-Separation-and-Side-Load-Behavior-of-Truncated-Ter
[14] TOMITA T,TAKAHASHI M,SASAKI M,et al.Experimental evaluation of side-loads in LE-7A prototype engine nozzle[J].Shock Waves,2009,19(3):213-228.
[15] FREY M,MAKOWKA K,AICHNER T.The TICTOP nozzle:A new nozzle contouring concept[J].CEAS Space Journal,2017,9(2):175-181.
[16] 刘亚洲,李平,陈宏玉,等.一种低空满流的大面积比液体火箭发动机喷管[J].推进技术,2022,43(10):205-212.
[17] 刘国球.液体火箭发动机原理[M].北京:中国宇航出版社,2005.
[18] 刘阳旻.液体火箭发动机喷管附面层求解器开发与应用[D].北京:中国运载火箭技术研究院,2021.
[19] NICKERSON G R,DANG L D,COATS D E,et al.Engineering and programming manual:Two-dimensional kinetic reference computer program[R].NAS8-35931.
[20] 孙得川,杨建文.液体火箭发动机喷管仿真模型[J].火箭推进,2022,48(2):56-65.
[21] 丁煜朔.液体火箭发动机喷管型面设计与传热仿真分析研究[D].北京:中国运载火箭技术研究院,2019.
[22] ALLAMAPRABHU C,RAGHUNANDAN B,MORÍÑIGO J A.Improved prediction of flow separation in thrust optimized parabolic nozzles with FLUENT[EB/OL].https://www.semanticscholar.org/paper/Improved-Prediction-of-Flow-Separation-in-Thrust-Allamaprabhu-Raghunandan/37d0bbb64d667f39bcf1bb45861cad3ce22df16e,2011.
[23] NICKERSON G,DANG L.Performance predictions for an SSME configuration with an enlarged throat[EB/OL].https://www.semanticscholar.org/paper/Performance-predictions-for-an-SSME-configuration-Nickerson-Dang/b6
[24] ZUCROW M J,HOFFMAN J D.Gas dynamics[M].New York:Wiley,1977.

备注

引言

1 常用钟型喷管型面设计

2 喷管性能和流动分离计算方法

3 计算结果

4 结论

期刊信息