摘要
两级入轨(TSTO)飞行器并联分离过程中,一级和二级飞行器之间存在激波多次反射,对飞行器的压力分布、力矩特性和飞行姿态会产生较大影响,甚至可能严重影响飞行器级间分离的安全性。基于自主开发的NNW-FlowStar软件和非结构混合网格自适应技术,对国家数值风洞工程自主设计的某两级入轨飞行器标模开展并联分离特性研究,并与风洞试验数据进行对比分析,从而验证了NNW-FlowStar软件模拟飞行器并联分离特性的可靠性和有效性。研究表明:NNW-FlowStar软件可以较好模拟两级入轨飞行器并联分离特性,数值模拟结果与试验结果吻合较好,计算得到的流场结构与风洞试验一致,采用网格自适应技术可以有效提升模拟精度。两级入轨飞行器并联分离过程会经历组合体流动、缝隙流动、小通道流动、大通道流动,最终到自由流动等不同的典型流动阶段,激波结构快速变化,存在激波/激波干扰、边界层/边界层干扰和激波/边界层干扰等复杂的流动现象。
During the parallel separation process of two stages to orbit(TSTO)vehicles,there are multiple reflections of shock waves between the first and second stage vehicles.The complex flow has a great impact on the pressure distribution,torque characteristics and flight attitude of the vehicles,and may even seriously affect the safety of the separation between stages of the vehicles.The parallel separation properties of the two stages to orbit vehicle model created by the National Numerical Wind Tunnel Project are examined using adaptation techniques for unstructured hybrid mesh and the self-developed National Numerical Wind Tunnel Project software,NNW-FlowStar.The simulation results are compared with the wind tunnel test data,and the reliability and effectiveness of NNWFlowStar simulation of parallel separation characteristics of vehicles are confirmed.The research shows that the NNW-FlowStar can better simulate the parallel separation characteristics of the two stages to orbit the vehicle.The numerical simulation results are in good agreement with the test results.The calculated flow field structure is consistent with the wind tunnel test.Using the mesh adaptive technology can effectively improve the simulation accuracy.T In order to circle the vehicle,the two stages will separate in parallel and travel through several typical flow stages,including combination flow,gap flow,small channel flow,big channel flow,and free flow.During the whole process,the shock structures change rapidly,and there are complex flow phenomena such as shock wave interference,boundary layer interference and shock wave/boundary layer interference.
作者
张培红
周桂宇
沈盈盈
唐静
赵炜
贾洪印
ZHANG Peihong;ZHOU Guiyu;SHEN Yingying;TANG Jing;ZHAO Wei;JIA Hongyin(Computational Aerodynamic Institute of China Aerodynamics Research and Development Center,Mianyang 621000,China)
出处
《北京航空航天大学学报》
北大核心
2025年第5期1620-1628,共9页
Journal of Beijing University of Aeronautics and Astronautics
基金
国家数值风洞工程。
