某运载火箭级间分离喷流干扰风洞试验研究

Wind tunnel test on effect of the jet flow interaction on stage separation of launch vehicle

对某运载火箭级间分离特性进行了风洞试验研究,内流采用冷喷流模拟技术,获得了助推器与芯级同时分离和助推器先分离时,两级在有、无喷流、同轴变迎角情况下的气动力系数,试验结果表明,助推器与芯级同时分离和助推器先分离两种情况下,一、二级箭体各自的气动力系数变化很小,这说明助推器与芯级同时分离的方案是可行的。风洞试验研究结果为运载火箭级间分离方案设计和火箭控制系统参数设计提供了依据。

This paper presents the wind tunnel test on aerodynamics of launch vehicle during stage separation. The method of cold jet is used to simulate internal flow. Satisfying test results and many flow filed configuration photographs have been obtained. The experimental data indicate that the aerodynamic difference between two cases of the first stage separation with or without booster is little, so the first stage and booster separation at same time is feasible. The tests results could be taken as a reference in the designing of launch vehicle.