氢氧发动机真空羽流干扰试验研究

为了研究航天器发动机多股羽流产生的羽流干扰对流场结构及参数的影响，在北京航空航天大学真空羽流效应试验系统（PES）中，采用总压皮托管阵列对60 N氢氧模拟发动机单机羽流和双机干扰羽流的压力场进行了测量。试验结果表明:单机羽流流场压力随着轴向距离的增大而迅速降低；受到钟形喷管产生的压缩波束影响，同一轴向距离上的压力最大值逐渐偏离喷管轴线；双机羽流干扰发生于两股发动机羽流主流之间的区域，干扰流的作用范围和强度随着轴向距离的增大而增大，干扰流压力最高可以达到单机羽流相同位置处压力的5倍以上；受到干扰流压缩波束边界的影响，同一轴向距离上的压力最大值逐渐偏离双发动机对称面。 

Experimental investigation on vacuum plume interaction of hydrogen/oxygen engines

To investigate the effects of plume interaction caused by multiple spacecraft engines on the flow field structure and parameters, the pressure fields of single plume and dual plumes generated by hydrogen/oxygen engines with 60 N thrust were determined using a pitot tube array in vacuum plume effect experimental system (PES) of Beihang University. The experimental results show that the pressure in the single plume field decreases rapidly with the increase of axial distance, and the location of the maximum pressure along the same axial distance gradually deviates from the nozzle axis due to the compression waves generated from the bell nozzle. Plume interaction occurs in the region between the dual prime plumes, whose action range and intensity increase with the increase of axial distance. To the highest degree, the pressure of the interacted plume can be more than 5 times that of the single plume at the same point. The location of the maximum pressure along the same axial distance gradually deviates from the symmetry plane of the dual engines due to the compression waves' boundary of the interacted plume.