火箭级间分离喷流干扰数值模拟与风洞试验研究

Numerical simulation and wind tunnel test research on rocket stage-separation jet flow interaction

针对典型风洞试验状态,采用有限体积法求解三维雷诺平均Navier-Stokes(RANS)方程,数值模拟了给定级间距下火箭级间分离喷流干扰流动情况,获得了清晰的流场结构和有/无喷流干扰时两级气动特性变化规律,并对仅主机喷流和主机与四游机同时喷流的情况进行了计算,数值模拟研究结果为风洞试验方案的设计提供了参考依据。在典型状态数值模拟研究的基础上采用了冷喷流模拟技术对多个状态下火箭级间分离喷流干扰特性进行了风洞试验研究,获得了两级在有/无喷流、同轴变攻角情况下的气动力系数,研究结果表明,级间喷流干扰会对两级气动特性带来较大影响。相同状态下计算得到的两级气动特性变化与试验符合较好,表明了针对风洞试验状态的预先数值模拟对试验方案的设计验证可提供有益的参考。

The paper presents wind tunnel test and numerical simulation research on aerodynamics of rocket during stage separation. Finite volume method is used to calculate the three-dimensional Reynolds- averaged Navier-Stokes equations in this paper. The typical stage-separation flow field of rocket is simulated, and reasonable flow structure is obtained. The numerical results show the aerodynamic characteristics variations of first and second stages and they conformed well to the experimental data. That the results with only main jet on are close to those with all jet on provides fine technical support for the experimental design in the wind tunnel. During the test, the method of cold jet is used to simulate internal flow. Satisfying test results and many flow filed configuration photographs have been obtained. The research results indicate that the stage jet flow interactions have heavy effects on aerodynamics of two stages. The combine of tests and numerical simulation results could be taken as a reference in the designing of rocket.