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某些应用条件下,飞行器需要RBCC发动机提供更大的推力,受飞行器/发动机一体化气动外形约束,冲压流道推力很难大幅提高,不得不提高火箭发动机推力。当火箭推力需求过大时,传统的在隔离段或燃烧室流道内布置火箭发动机的方法受限于狭小的空间约束,火箭发动机设计难度增加,性能降低。为此,提出了一种将火箭发动机布置于冲压发动机尾喷管侧壁的方法,并开展了火箭状态对尾喷管性能影响的初步研究。结果表明:这种布置方式充分利用尾喷管较大的几何空间,火箭射流可在尾喷管内继续膨胀,不仅不会削弱尾喷管的推力性能,甚至可以产生额外的推力增量,且其升力会大幅增加。此外,该方式还可实现火箭发动机大推力和高比冲的较好匹配,其应用也可拓展至RBCC发动机外的相似领域。
Under some application conditions, the aircraft needs an RBCC engine to provide greater thrust and is constrained by the integrated aerodynamic shape of the aircraft / engine. As a result, it is difficult to significantly increase the thrust of the ramjet and increase the thrust of the rocket engine. When the rocket thrust demand is too large, the traditional method of arranging the rocket motor in the isolation section or the combustion chamber flow channel is limited by the small space constraint, and the rocket engine design difficulty increases and the performance decreases. Therefore, a method of arranging the rocket motor on the side wall of the tail pipe of a stamped engine is proposed and a preliminary study on the influence of the rocket status on the performance of the tail pipe is carried out. The results show that this arrangement makes full use of the large geometric space of the nozzle and the rocket jet can continue to expand in the nozzle without impairing the thrust performance of the nozzle and even generating additional thrust increment Lift will increase dramatically. In addition, this method can also achieve a good match between rocket motor thrust and high specific impulse, and its application can be extended to similar fields outside the RBCC engine.