Numerical simulation analysis on aerodynamic characteristics of TSTO interstage separation

GONG Xiaoquan; JIA Hongyin; ZHAO Hui; TANG Jing; ZHANG Jian; FU Yunfeng

doi:10.7638/kqdlxxb-2022.0025

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Numerical simulation analysis on aerodynamic characteristics of TSTO interstage separation

更新时间：2026-05-28

- Numerical simulation analysis on aerodynamic characteristics of TSTO interstage separation
- Vol. 41, Issue 5, Pages: 109-118(2023)
- 作者机构：
  
  1. 中国空气动力研究与发展中心计算空气动力研究所,绵阳,621000
  2. 空气动力学国家重点实验室,绵阳,621000
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2022.0025
  CLC： V211.3
- Published：2023
- 稿件说明：
移动端阅览
龚小权, 贾洪印, 赵辉, 等. TSTO级间分离气动特性数值仿真分析[J]. 空气动力学学报, 2023, 41(5): 109−118.

GONG Xiaoquan, JIA Hongyin, ZHAO Hui, et al. Numerical simulation analysis on aerodynamic characteristics of TSTO interstage separation[J]. 2023, 41(5): 109-118.
龚小权, 贾洪印, 赵辉, 等. TSTO级间分离气动特性数值仿真分析[J]. 空气动力学学报, 2023, 41(5): 109−118. DOI： 10.7638/kqdlxxb-2022.0025

GONG Xiaoquan, JIA Hongyin, ZHAO Hui, et al. Numerical simulation analysis on aerodynamic characteristics of TSTO interstage separation[J]. 2023, 41(5): 109-118. DOI： 10.7638/kqdlxxb-2022.0025.

摘要

两级入轨（TSTO）重复使用飞行器并联级间分离是一二级飞行器设计必须考虑的关键因素。采用国家数值风洞工程通用CFD软件NNW-FlowStar，基于各向异性非结构混合网格及重叠网格技术，研究了TSTO在侧滑角下的并联级间分离过程。软件通过自主改进的Roe熵修正方法、节点高斯梯度算法实现高超声速流场的精细模拟，运用“物面相交”准则实现多套网格间的并行挖洞。采用双时间步求解非定常分离过程，内迭代计算采用LU-SGS方法。文中首先采用WPFS投放标模验证了软件在常规分离投放方面的数值模拟精度；然后模拟获得TSTO组合体定常气动特性，分析了不同攻角下一二级的气动特性以及可能的安全分离状态；最后数值模拟了TSTO在负攻角、正侧滑角下的并联级间分离过程，与对应的CTS试验结果比较，两级质心位移的计算值和实验值随时间变化具有很好的一致性，偏航角及俯仰角在变化规律和量值上比较吻合，表明软件具备升力体并联级间分离类问题的数值模拟能力。

Abstract

Parallel interstage separation of the two stage to orbit (TSTO) reusable launch vehicle (RLV) is a key factor to be considered in the design of two-stage aircraft. Using the general computational fluid dynamics (CFD) software

NNW-FlowStar developed by the national numerical wind-tunnel (NNW) project

the parallel interstage separation process of TSTO under sideslip angles was studied with the anisotropic unstructured grid and overlapping grid technology. The software simulated details of the hypersonic flow field through independently improved Roe entropy correction method and node Gaussian gradient algorithm

together with the wall criterion applied during the automatic hole-cutting procedure. The dual-time method was used to solve the unsteady separation process

and the LU-SGS algorithm was adopted for the internal iteration calculation. Firstly

the WPFS standard model was simulated to verify the accuracy of the software. Then the steady aerodynamic characteristics of the TSTO assembly were obtained and analyzed for the first and second stages at different angles of attack and possible safe separation states. Finally

the separation process of TSTO under a negative angle of attack and a positive sideslip angle was numerically simulated

and the time variations of the centroid displacement and attitude angle of the two stages were compared with the CTS experimental results

which showed a good agreement. The present study suggests that NNW-FlowStar can well simulate the interstage separation process of parallel aircraft.

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Keywords

references

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