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为研究固体火箭发动机激波诱导矢量控制效率的影响因素,及验证数值模拟方法的准确性,对激波诱导轴对称推力矢量喷管模型进行了壁面测压试验,采用二阶精度Roe格式和k-ωSST两方程湍流模型求解强守恒型Navier-Stokes方程对矢量喷管复杂干扰内流场进行数值模拟。根据试验和数值模拟结果分析了喷管内主流和次流相互作用产生的复杂流场结构,比较了在不同喷管落压比NPR和次主流压力比SPR下喷管壁面静压的分布情况。结果表明,数值计算和试验结果基本吻合,验证了计算方法的准确性;在一定范围内减小喷管落压比,增大次主流压力比可以增大喷管周向壁面静压差,提高喷管的推力矢量偏角。
In order to study the influencing factors of shock induced vector control efficiency of solid rocket motor and to verify the accuracy of the numerical simulation method, the wall pressure test of shock induced axial symmetrical thrust vector nozzle model was carried out. The second order accuracy Roe format and k -ωSST two-equation turbulence model strong Conservative Navier-Stokes equations for the numerical simulation of vector nozzle complex interference flow field. According to the experimental and numerical simulation results, the complicated flow field structure of the interaction between the main flow and the secondary flow in the nozzle was analyzed. The static pressure distribution on the nozzle wall was compared under different nozzle pressure ratio NPR and sub-mainstream pressure ratio SPR. The results show that the numerical calculation is in good agreement with the experimental results, which verifies the accuracy of the calculation method. It can reduce the nozzle down-pressure ratio and increase the sub-mainstream pressure ratio within a certain range to increase the static pressure difference of the nozzle circumferential wall, Thrust vector nozzle angle.