为确定双燃烧室火箭发动机的工作特点而进行了一次实验研究。本实验用轴对称和二维试验装置,用空气流模拟了其实际流动情况。并不需要专门的设计,总可以使主发动机排气流在助推器内腔中发生骤降(除长度很短的助推器以外),人们已发现,在发生骤降时,推力对助推器空腔长度不敏感。选用适当的喷管喉部面积比值和助推器直径就可以在助推器内腔中保持超音速流动,并使推力显著地增加。设计一台以超音速流动方式工作的实际发动机,特别是无喷管助推器的发动机看来是切实可行的。 An experimental study was conducted to determine the characteristics of a dual-chamber rocket engine. In this experiment, the axial flow and the two-dimensional test device were used to simulate the actual flow condition with air flow. No special design is required and the main engine exhaust flow can always be caused to plunge in the booster cavity (except for the very short booster). It has been found that in the event of a sudden drop in thrust, Slider cavity length insensitive. Using the appropriate nozzle throat area ratio and booster diameter, supersonic flow can be maintained in the booster lumen with a significant increase in thrust. It would seem feasible to design a real engine that works in supersonic flow, especially a nozzleless booster.