水平并联TBCC冲压喷管调节方案设计及性能研究

Design and Performance Research of Adjustable Mechanism of Horizontal Layout Parallel TBCC Exhaust System

为了研究不同冲压喷管几何调节方案对某卧式水平并联TBCC排气系统在其全飞行包线范围内一体化性能的影响规律,开展不同冲压喷管调节方案的并联TBCC排气系统的数值模拟对比研究,确定排气系统的最佳构型,获得典型工况下排气系统一体化性能参数的变化规律和其内外耦合流场结构。结果表明:能一定程度控制出口面积的冲压喷管调节方案对应的排气系统一体化性能最好;采用最佳调节方案的排气系统在冲压喷管单独工作阶段的一体化推力系数保持在0.97左右;水平并联TBCC排气系统膨胀面的法向力能够相互抵消,从而有效地解决了上、下并联TBCC排气系统升力突变而引起的飞行控制难题。

In order to explore the influence of different ramjet nozzle geometric regulation schemes on the integrated performance of horizontal parallel TBCC exhaust system in the whole flight envelope range,a comparative numerical simulation study of parallel TBCC exhaust system with different ramjet nozzle regulation schemes was carried out.The optimal configuration and aerodynamic scheme of the exhaust system were determined,and the variation rule of integrated performance parameters and the structure of internal and external coupling flow field of the parallel TBCC exhaust system under typical working conditions were obtained.The results show that the ramjet nozzle regulation scheme with controlling outlet area corresponding exhaust system has the best integrated performance,and the integrated thrust coefficient of the exhaust system of the best solution can be maintained at about 0.97 in the single working stage of the ramjet nozzle,and the normal forces on the expansion surface of the horizontal parallel TBCC exhaust system cancel each other out,which effectively solves the flight control problem caused by the sudden change of lift force of the up and under parallel TBCC exhaust system.