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利用自行设计的烤燃实验装置,对HTPE推进剂小尺寸烤燃试样分别进行了升温速率为1、2℃/min的烤燃实验,以此为基础,建立了小尺寸烤燃试样和固体火箭发动机的三维计算模型,利用Fluent软件分别对两者不同升温速率下的烤燃行为进行了数值模拟计算,研究了小尺寸烤燃试样与固体火箭发动机的装药尺寸及结构差异对HTPE推进剂烤燃响应特性的影响。结果表明,HTPE推进剂的烤燃响应时间、响应温度随升温速率的变化趋势与装药尺寸及结构无关,但响应时间和响应温度的绝对值与装药尺寸及结构均有很大关系,升温速率为3.3℃/h(0.055℃/min)时,小尺寸烤燃试样的响应时间为40.3h,响应温度为158℃,而固体火箭发动机响应时间为28.83h,响应温度为120.13℃。推进剂装药尺寸及结构对烤燃点火位置有明显影响,进而影响到烤燃速度范畴的区分,小尺寸烤燃试样慢烤升温速率不大于2℃/min,而固体火箭发动机慢烤升温速率为小于0.5℃/min。因此,对快速、慢速烤燃的严格划分,必须结合装药尺寸、装药结构及推进剂种类等因素进行。升温速率对固体火箭发动机存在热积累临界位置效应,本研究条件下影响热积累临界位置的升温速率为0.5℃/min。
Based on the self-designed roasting and burning experiment device, the experiment of baking and burning of the HTPE propellant small-scale roasted and burned samples was respectively carried out at a heating rate of 1,2 ℃ / min. Based on this, Solid rocket motor three-dimensional calculation model, Fluent software were used to simulate the flue-burning behavior of the two under different heating rates respectively. The influence of the size and structure difference of the charge on the small size baked solid rocket engine and the solid rocket motor on HFPE Effects of Propellants on Firing Characteristics. The results show that the response time and response temperature of the HTPE propellant have no relation with the size and structure of the charge, but the absolute value of the response time and the response temperature have a great relationship with the size and structure of the charge. At the rate of 3.3 ℃ / h (0.055 ℃ / min), the response time was 40.3h and the response temperature was 158 ℃. The solid rocket motor response time was 28.83h and the response temperature was 120.13 ℃. The size and structure of the propellant charge have a significant effect on the ignition position of the fuming and burning, which in turn affects the distinction between the firing rate and the firing rate. The slow baking rate of the small size fuming combustion sample is not more than 2 ℃ / min, while the solid rocket motor slowly roasts The rate is less than 0.5 ° C / min. Therefore, the strict division of fast and slow burning must be based on factors such as the size of the charge, the structure of the charge, and the type of propellant. The heating rate has a heat accumulation critical position effect on the solid rocket motor. Under this research condition, the heating rate that affects the critical position of heat accumulation is 0.5 ℃ / min.