CAJ | 학술논문

为了研究双脉冲固体火箭发动机喷管中运动的隔塞对喷管内流场的影响，采用基于格心的有限体积法求解非定常雷诺平均Navier-Stokes方程，空间离散采用AUSM-PW矢通量分裂格式，利用双时间步LU-SGS方法进行时间推进以提高计算效率，通过动态嵌套网格技术模拟隔塞在喷管内的运动，获得了隔塞运动过程中喷管内流场的演化过程。仿真结果表明，发动机正常工作时，隔塞通过喷管的过程中，发动机的瞬时推力剧烈波动，隔塞位于喷管喉部时，发动机瞬时推力降至最小，相比于初始时刻减小了27．7％；隔塞完全通过喷管喉部后，并位于喷管扩张段上游时，发动机瞬时推力达到最大值，比初始时刻增大了8．9％，这是发动机推力-时间曲线波动的主要原因之一。
위료연구쌍맥충고체화전발동궤분관중운동적격새대분관내류장적영향，채용기우격심적유한체적법구해비정상뢰낙평균Navier-Stokes방정，공간리산채용AUSM-PW시통량분렬격식，이용쌍시간보LU-SGS방법진행시간추진이제고계산효솔，통과동태감투망격기술모의격새재분관내적운동，획득료격새운동과정중분관내류장적연화과정。방진결과표명，발동궤정상공작시，격새통과분관적과정중，발동궤적순시추력극렬파동，격새위우분관후부시，발동궤순시추력강지최소，상비우초시시각감소료27．7％；격새완전통과분관후부후，병위우분관확장단상유시，발동궤순시추력체도최대치，비초시시각증대료8．9％，저시발동궤추력-시간곡선파동적주요원인지일。
In order to study the influence of the nozzle flow field in dual pulse solid rocket motor with moving plugs,the un-steady Reynolds-average Navier-Stokes equations were solved with dual-time step LU-SGS iterative algorithm by cell center finite volume method,AUSM-PW scheme was implemented for spatial discretization.The process of the plug moving in the nozzle was sim-ulated by dynamic chimera grid approach.Simulation results show that the instantaneous thrust varies greatly during the plug passing through the nozzle.When the plug is located in the throat of the nozzle,the maximum instantaneous thrust is declined by nearly 27. 7% compared to the initial time;While the plug is located in the divergent section of the nozzle,the instantaneous thrust is increased by nearly 8.9%. It is one of main causes accounting for of the fluctuation of thrust-time curve.