高超声速一体化飞行器推阻特性测量研究

利用飞行器和发动机研究成果，设计了能在0600mm脉冲燃烧风洞开展试验研究、基本满足推阻平衡要求的缩比机体／推进一体化飞行器模型，利用0600mm脉冲燃烧风洞，完成了带动力一体化飞行器推阻特性的试验研究。设计了组合式三分量一体化飞行器测力天平，在以氢气为燃料、发动机工作时（油气比约为1．2），一体化飞行器模型推力与阻力相当，飞行器实现了推阻平衡。试验表明，飞行器和发动机匹配良好，发动机实现了点火和稳定燃烧，并取得了较高的推力收益，较好地验证了超燃冲压发动机和一体化飞行器设计和计算分析预测的有效性，为大尺度飞行器测力研究奠定了技术基础。

Experimental investigation on thrust-drag performance of hypersonic integrative vehicle

In this paper, a reduced scale hypersonic flame/propulsion integrative vehicle model was designed on the basis of research achievement of scramjet and vehicle, and the test of measuring thrust/drag performance of the vehicle was accomplished in the φ600mm impulse combustion wind-tunnel, and an assembled three component balance was designed to measure the thrust/drag of the vehicle. When the scramjet working with hydrogen （the fuel/air equivalence ratio was about 1.2） the thrust of the scramjet was equal to the drag of the vehicle, the thrust/drag balance was achieved. The results of the test indicated that the scramjet and the vehicle were matched perfectly, the scramjet was self-ignition and high thrust augmentation was obtained. And the methods of designing and analyzing of the scramjet/vehicle were checked, the measuring thrust/ drag performance of the full scale vehicle was established.