通过调节喷管喉部面积,可使单室双推力固体火箭发动机在较小的压强比下,产生更大的推力比,提升固体火箭发动机的综合性能。文中介绍了一种单室双推力固体火箭发动机喷管喉道面积调节机构,可利用火箭发动机自身燃气压强形成压强差驱动调节机构,完成喷管喉部面积的调节。文中详细论述了机构的工作原理,通过工作过程仿真和模拟试验验证了其工作机理的可行性,喷管有结构简单、易于实现的优点。

By adjusting nozzle throat area, a sin gle-chamber dual-thrust solid rocket motor can produce more thrust ratio with a smaller pressure ratio to enhance overall performance of the solid rocket motor. In the paper, a nozzle throat area adjustment mechanism of a sin gle-chamber dual-thrust solid rocket motor was described. The pressure difference based on the gas pressure of the rocket motor itself can be obtained in the adjustment mechanism to drive the adjustment device, thereby completing the throat area control. The working principle of the adjustment mechanism was discussed in detail and its feasibility was verified through the work process simulation and simulation test., the nozzle investigated in this paper has advantages including simple structure and easy realization.