Single-chamber double-thrust solid rocket engine with high thrust ratio

The invention discloses a single-chamber double-thrust solid rocket engine with a high thrust ratio. The single-chamber double-thrust solid rocket engine at least comprises a charging combustion chamber, a spray pipe, an ignition device and a throat adjusting mechanism. The charging combustion chamber at least comprises a heat insulation top cover, a heat insulation shell, a cruising grain and a boosting grain. The spray pipe at least comprises a convergent section pipe body, an expansion section pipe body, a backing and a throat liner. The ignition device is arranged at the left end of the convergent section pipe body; the throat adjusting mechanism is arranged in the convergence section pipe body and at least comprises a supporting body and a telescopic body. The large thrust ratio can be achieved, and the cruise level specific impulse is improved. 本申请公开了一种大推力比的单室双推力固体火箭发动机，至少包括：装药燃烧室、喷管、点火装置和喉部调节机构；其中，装药燃烧室至少包括：绝热顶盖、绝热壳体、巡航药柱和助推药柱；喷管至少包括：收敛段管体、扩张段管体、背衬和喉衬；点火装置设置于收敛段管体的左端；喉部调节机构设置于收敛段管体内部，喉部调节机构至少包括：支撑本体和伸缩