齐治 1王国华 2武学安 2孙全福 2周柏航 3王浩 1阮文俊1
作者信息
- 1. 南京理工大学能源与动力工程学院,江苏 南京 210094
- 2. 中国兵器工业集团航空弹药研究院有限公司,黑龙江 哈尔滨 150010
- 3. 中国工程物理研究院流体物理研究所,四川 绵阳 621999
- 折叠
摘要
Abstract
To investigate the complex wake flow characteristics of multi-motor parallel rocket sleds,this study focuses on the mechanisms by which the nozzle horizontal spacing and the impingement height influence the flow structure and ground effect.A three-dimensional physical model was constructed for a dual-rail rocket sled system featuring three nozzles arranged in a triangular pyramid configuration.Four operating conditions were established,including large spacing(s=7d),small spacing(s=1d),low impingement height(h=2d),and high impingement height(h=5.5d).Here,s represents the horizontal center-to-center distance of the nozzles,h denotes the impact height,and d signifies the diameter of the nozzle outlet.The effects of nozzle center distance and impingement height on the flow field structure and ground effect were comparatively analyzed.Numerical simulations were performed using a computational fluid dynamics(CFD)method based on the Reynolds-Averaged Navier-Stokes equations,coupled with the Realizable k-ε turbulence model for transient solutions.The combustion chamber pressure-time curve derived from interior ballistic theory was applied to the nozzle inlet via a user-defined function(UDF).The sled velocity-time curve,determined from the exterior ballistic particle trajectory equation,was assigned as the far-field pressure boundary condition,enabling a coupled simulation framework of interior ballistics,exterior ballistics and flow field.The computational domain utilized a structured grid with refinement in the jet interaction region and near the ground to ensure calculation accuracy.The velocity and pressure fields obtained from numerical simulations were compared and validated against jet morphology,impingement height,and vortex core positions recorded by high-speed photography(2 000 Hz).The flow field structure,pressure distribution,and thermal erosion behavior on the ground under different configurations are systematically revealed.The results indicate that the small-spacing nozzle arrangement triggers intense jet interference without ground effect participation,leading to a multi-peak and slow-recovery pressure evolution feature and substantially delays the flow field relaxation process.The coupling relationship between ground effect and jet interference is dominated by impingement height.At low impingement height conditions,the jet impinging on the ground induces intense reorganization and fragmentation of vortex structures,generating wall jets with velocities up to 960 m/s.Consequently,the peak ground surface temperatures reaches 1 286.6 K with sustained high temperatures,which significantly elevates the risk of rail ablation.Conversely,a high impingement height effectively suppresses the ground effect,resulting in a more homogeneous and stable flow field structure.In this case,the peak ground temperature reduced by approximately 65%and maximum velocity reduced by 58%,significantly mitigating ablation risk.The initial phase(0-8 m)of the rocket sled is identified as the critical region subjected to the most severe thermomechanical loads.During this stage,the average acceleration reaches 832.7 m/s2,and the specific action time per unit distance is prolonged to 1.84 ms/m.Coupled with the transient complex flow field,this constitutes an extremely high risk for rail ablation.The numerical simulation results show excellent agreement with high-speed photographic experimental data regarding flow field morphology,impingement height,and vortex core positions,thereby validating the reliability of the established coupled model.This study elucidates the complex flow mechanisms of multi-nozzle parallel systems under strongly constrained conditions,and provids important theoretical foundations and design parameters for structural layout optimization and thermal protection design in high-acceleration,heavy-load rocket sled test systems.关键词
火箭橇试验/火箭发动机/三维数值仿真/喷管流场/流场地面效应Key words
rocket sled test/rocket motor/3D numerical simulation/nozzle flow field/ground effect of flow field分类
数理科学
