固体推进剂装药固化降温时间估算新法

CALCULATION FOR THE AFTER-CURE COOLING TIME OF CAST-MODIFIED-DOUBLE-BASE PROPELLANTS

对大型固体火箭发动机浇铸装药的固化降温时间提出一种新的估算方法。该方法根据不稳定热传导方程计算装药内部各点温度分布和所需降温时间，由所需降温时间计算出对应的应力松弛模量。并与实验的松弛模量谱比较，在该降温时间内应力是否达到完全松弛。

An unsteady heat conduction model is proposed to calculate the temperature distribution of the case-bonded rocket motor and the time required for the cooling process based on the experimentally determined thermal and mechanical parameters of the cast-modified-double-base propellant(CMDB) and its fiberglass epoxy shell.The resultant value of the time is then used to derive the corresponding stress relaxation modulus,which is compared with the modulus data obtained from uniaxial tensile stress relaxation experiments to see if the internal stress has been thoroughly relaxed within this period of time