多种组合动力方案性能对比研究

针对目前国内外不同的TBCC组合动力概念方案进行了性能对比研究，主要包括:涡轮/亚燃冲压/双模态超燃冲压组合发动机、涡轮/引射冲压/双模超燃冲压组合发动机、射流预冷涡轮/双模态超燃冲压组合发动机和空气涡轮火箭/双模态超燃冲压组合发动机。通过发动机性能计算，获得了不同方案的高度、速度特性；基于马赫数6.5高超声速巡航飞行器相同的飞行任务和气动特性，计算比较了不同动力方案的飞行器航程、巡航距离和加速时间等性能参数。结果表明:涡轮/亚燃冲压/双模态超燃冲压组合发动机在4种方案中比冲最高；在相同的翼载和起飞推重比下，涡轮/亚燃冲压/双模态超燃冲压组合发动机具有最大的航程和巡航距离，但爬升加速时间最长；空气涡轮火箭/双模态超燃冲压组合发动机的航程和巡航距离最短，但加速性能较高，爬升加速时间最短。

Compared study of performances of combined cycle engines

Performances of different combined cycle engine concepts, including Turbine/Ramjet/Dual-mode Scramjet (TE/RJ/DMSJ), Turbine/Ejector Ramjet/Dual-mode Scramjet(TE/ERJ/DMSJ), Pre-cooled Turbine/Dual-mode Scramjet (PCTE/DMSJ) and Air-turbo-rocket/Dual-mode Scramjet (ATR/DMSJ), are studied. The altitude-velocity characteristics of the combined cycle engines are obtained. Based on the same mission and aerodynamic characteristics of a hypersonic vehicle capable of Ma 6.5 cruise, the range, cruise distance and acceleration time are calculated of the vehicle by using the different combined cycle engines. The results indicate that the TE/RJ/DMSJ has the highest specific impulse among the four kinds of engines. The vehicle has the longest range and acceleration time by using TE/RJ/DMSJ under the same thrust loading and wing loading and it has the shortest range and acceleration time by using ATR/DMSJ.