A mesh adaptation method for TSTO stages separation CFD simulation

TANG Jing; ZHANG Jian; ZHANG Yaobing; ZHOU Naichun; LIU Gang

doi:10.7638/kqdlxxb-2022.0028

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

A mesh adaptation method for TSTO stages separation CFD simulation

更新时间：2026-05-28

- A mesh adaptation method for TSTO stages separation CFD simulation
- Vol. 41, Issue 6, Pages: 102-108(2023)
- 作者机构：
  
  中国空气动力研究与发展中心,绵阳,621000
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2022.0028
  CLC： V211.3;V411.3
- Published：2023
- 稿件说明：
移动端阅览
唐静, 张健, 张耀冰, 等. 一种用于TSTO级间分离CFD计算的网格动态优化技术[J]. 空气动力学学报, 2023, 41(6): 102−108.

TANG Jing, ZHANG Jian, ZHANG Yaobing, et al. A mesh adaptation method for TSTO stages separation CFD simulation[J]. 2023, 41(6): 102-108.
唐静, 张健, 张耀冰, 等. 一种用于TSTO级间分离CFD计算的网格动态优化技术[J]. 空气动力学学报, 2023, 41(6): 102−108. DOI： 10.7638/kqdlxxb-2022.0028

TANG Jing, ZHANG Jian, ZHANG Yaobing, et al. A mesh adaptation method for TSTO stages separation CFD simulation[J]. 2023, 41(6): 102-108. DOI： 10.7638/kqdlxxb-2022.0028.

摘要

两级入轨空天运输系统具有难度较低和经济性好的优点，级间分离是该运输系统设计的一项关键技术。相比前后串联级间分离，两级入轨上下两级间存在严重的激波相互干扰，直接影响分离物体的气动力矩。为了更好地模拟分离过程中两级之间的运动激波多次反射问题，本文结合非结构混合网格分布优化技术和压力比值激波识别技术，建立了用于级间分离运动过程的并行网格动态优化技术。基于计算流体力学软件NNW-FlowStar，完成了两级入轨运输系统并联分离过程的数值模拟。结果表明，采用网格动态优化技术，可实现级间复杂激波的精细捕捉，更精准地获得了强干扰下飞行器的气动特性，显著提高了并联分离过程中运动轨迹和姿态的预测精度。

Abstract

The transport system of two-stages-to-orbit (TSTO) has many advantages

such as easy to implement and much less expensive. Successful separation between the two stages is a critical issue to design a TSTO transport system. Compared to a regular concatenation configuration with the front and back in-line layout

there is serious shock interference between the two stages of the TSTO parallel configuration

which obviously changes the aerodynamic moment of stages and consequently affects the attitude of upper stage during the separation procedure

such as the pitch angle. In order to simulate the multiple reflections of the moving shock wave between two stages in the separation process

a parallel mesh dynamic optimization technique for the separation process is established by combining the unstructured hybrid mesh distribution optimization technique and the pressure ratio based shock wave identification technique. The whole separation procedure was numerically simulated using the general computational fluid dynamics (CFD) software NNW-FlowStar. The results show that with mesh adaptation techniques

the complicated shocks between the two stages can be precisely captured

the more accurate aerodynamic moment can be obtained by CFD and hence the prediction precision of the trajectory and attitude can be improved significantly.

关键词

Keywords

references

ZHANG G C, YAO Y L, WANG H. A survey on development of two-stage-to-orbit horizontal-takeoff-horizontal-landing reusable launch vehicle in USA[J]. Aircraft Design, 2018, 38(2): 1-6 (in Chinese). [知网中文][知网英文]

LI B, TANG J, ZHOU N C. Numerical simulation of missile launching with rudder deflection[J]. Transactions of Nanjing University of Aeronautics Astronautics, 2013, 30(2): 107-115.

CUI P C, DENG Y Q, TANG J, et al. Adjoint equations-based grid adaptation and error correction[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(10): 2992-3002(in Chinese). [万方]

ALAUZET F, LOSEILLE A. A decade of progress on anisotropic mesh adaptation for computational fluid dynamics[J]. Computer-Aided Design, 2016, 72: 13-39. DOI:10.1016/j.cad.2015.09.005[LinkOut]

SLOTNICK J, KHODADOUST A, ALONSO J, et al. CFD vision 2030 study: a path to revolutionary computational aerosciences[J]. Mchenry county natural hazards mitigation plan, 2014.

TSOLAKIS C, CHRISOCHOIDES N, PARK M A, et al. Parallel anisotropic unstructured grid adaptation[J]. AIAA Journal, 2021, 59(11): 4764-4776. DOI:10.2514/1.J060270[LinkOut]

JOUBARNE E, GUIBAULT F, BRAUN O, et al. Numerical capture of wing tip vortex improved by mesh adaptation[J]. International Journal for Numerical Methods in Fluids, 2011, 67(1): 8-32. DOI:10.1002/fld.2103[LinkOut]

MOIGNE Y L. Adaptive mesh refinement sensors for vortex flow simulations[C]//ECCOMAS2004-European Congress on Computational Methods in Applied Sciences and Engineering, 2004.

BONFIGLIOLI A, PACIORRI R, DI MASCIO A. The role of mesh generation, adaptation, and refinement on the computation of flows featuring strong shocks[J]. Modelling and Simulation in Engineering, 2012, 2012(1): 1-15. DOI:10.1155/2012/631276[LinkOut]

GALIMOV A Y, SAHNI O, LAHEY R T Jr, et al. Parallel adaptive simulation of a plunging liquid jet[J]. Acta Mathematica Scientia, 2010, 30(2): 522-538. DOI:10.1016/S0252-9602(10)60060-4[LinkOut]

TODARELLO G, VONCK F, BOURASSEAU S, et al. Finite-volume goal-oriented mesh adaptation for aerodynamics using functional derivative with respect to nodal coordinates[J]. Journal of Computational Physics, 2016, 313: 799-819. DOI:10.1016/j.jcp.2016.02.063[LinkOut]

GNOFFO P, WHITE J. Computational aerothermodynamic simulation issues on unstructured grids[C]// 37th AIAA Thermophysics Conference, Portland, Oregon. Reston, Virginia: AIAA, 2004: 2371. doi: 10.2514/6.2004-2371

TANG J, ZHANG J, LI B, et al. Unsteady flow simulation with mesh adaptation[J]. International Journal of Modern Physics B, 2020, 34(14n16): 2040080. DOI:10.1142/s0217979220400809[LinkOut]

LUO Y X, FIDKOWSKI K. Output-based space-time mesh adaptation for unsteady aerodynamics[C]// 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Orlando, Florida. Reston, Virginia: AIAA, 2011: 491. doi: 10.2514/6.2011-491

TANG J, CUI P C, JIA H Y, et al. Robust adaptation techniques for unstructured hybrid mesh[J]. Acta Aeronautica et Astronautica Sinica, 2019, 40(10): 75-88(in Chinese). [万方]

唐静, 崔鹏程, 贾洪印, 等. 非结构混合网格鲁棒自适应技术[J]. 航空学报, 2019, 40(10): 122894. TANG J, CUI P C, JIA H Y, et al. Robust adaptation techniques for unstructured hybrid mesh[J]. Acta Aeronautica et Astronautica Sinica, 2019, 40(10): 122894. (in Chinese)[知网vs万方]

SCHLOEGEL K, KARYPIS G, KUMAR V. Wavefront diffusion and LMSR: algorithms for dynamic repartitioning of adaptive meshes[J]. IEEE Transactions on Parallel and Distributed Systems, 2001, 12(5): 451-466. DOI:10.1109/71.926167[LinkOut]

TANG J, ZHANG J, LI B, et al. Parallel algorithms for unstructured hybrid mesh adaptation[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(1): 91-100(in Chinese). [万方]

CHEN J Q, WU X J, ZHANG J, et al. FlowStar: general unstructured-grid CFD software for national numerical windtunnel (NNW)project[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(9): 1-22(in Chinese). [万方]

CHEN J T, ZHANG Y B, ZHOU N C, et al. Numerical investigations of the high-lift configuration with MFlow solver[J]. Journal of Aircraft, 2015, 52(4): 1051-1062. DOI:10.2514/1.C033143[LinkOut]

ROE P L. Approximate Riemann solvers, parameter vectors, and difference schemes[J]. Journal of Computational Physics, 1981, 43(2): 357-372. DOI:10.1016/0021-9991(81)90128-5[LinkOut]

KIM J, KWON O. Improvement on block LU-SGS scheme for unstructured mesh Navier-Stokes computations[C]// 40th AIAA Aerospace Sciences Meeting Exhibit, Reno, NV. Reston, Virginia: AIAA, 2002: 1061. doi: 10.2514/6.2002-1061

CHEN J T. The effects of turbulence model corrections on drag prediction of NASA common research model[C]// 32nd AIAA Applied Aerodynamics Conference, Atlanta, GA. Reston, Virginia: AIAA, 2014: 3171. doi: 10.2514/6.2014-3171

LIN J Z. China's first hypersonic wind tunnel dual CTS test capability formed in CARDC[J]. Journal of Experiments in Fluid Mechanics, 2021, 35(1): 126(in Chinese). [知网中文][知网英文]

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Separation trajectory safety evaluation platform based on embedded neural network data prediction

Experimental analysis of interference characteristics of TSTO stage separation based on PSP/TSP measurement

Dual-body synchronous captive trajectory test technique in hypersonic wind tunnel

Conceptual design of TBCC based TSTO configurations for stage seperation investigation

Positivity-preserving strategies and their comparision based on staggered CPR methods

Related Author

XIE Futian

ZOU Dongyang

WANG Yan

LIN Jingzhou

WU Anping

CHEN Lei

PENG Di

LIN Jingzhou

Related Institution

中国空气动力研究与发展中心超高速空气动力研究所

飞行器流体物理全国重点实验室

南京航空航天大学航空学院

Hypervelocity Aerodynamics Institute of China Aerodynamics Research and Development Center, Mianyang

School of Mechanical and Power Engineering, Shanghai Jiaotong University, Shanghai

AI问答

⁰