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为了研究固体火箭发动机气动喉部推力调节的一般规律,利用氮气作为介质对气动喉部喷管进行了冷流实验研究。研究了该种喷管的扼流性能,二次流嘴的面积、个数对其扼流性能的影响以及空腔容积与喷管压强调节时间的关系。掌握了气动喉部喷管的有效喉部面积随流量比变化的一般规律。结果表明,二次流与主流流量比越大,气动喉部面积越小。小的面积比具有更高的扼流性能,而当流量比大于0.4时,面积比对扼流性能无明显影响。空腔体积越小压强调节时间越短。
In order to study the general rule of pneumatic throat thrust regulation of solid rocket motor, the cold throat experiment of pneumatic throat nozzle was carried out using nitrogen as the medium. The choke performance, the area and number of secondary nozzles on the choke performance and the relationship between cavity volume and nozzle pressure regulation time were studied. Mastered the pneumatic throat nozzle effective throat area with the flow rate ratio of the general rule. The results show that the larger the ratio of the secondary flow to the mainstream flow, the smaller the aerodynamic throat area. Small area ratio has a higher choke performance, and when the flow ratio is greater than 0.4, the area ratio has no significant effect on the choke performance. The smaller the cavity volume, the shorter the pressure regulation time.