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利用热传导理论对发射装药保温过程中的传热特性进行分析,通过传热学计算和测试手段确定有关参数。利用三维实体建模软件Solidworks建立发射装药实体模型,通过ANSYS有限元仿真分析软件对发射装药内部温度传递变化规律进行仿真,得到了发射装药温度场分布与保温时间的关系及发射装药保透所需时间。结果证明了现行军标规定保温时间确有很大压缩空间。
Heat transfer theory is used to analyze the heat transfer characteristics of the propellant in the process of heat preservation. The relevant parameters are determined through heat transfer calculation and test. The solid propellant model was established by using solidworks modeling software SolidWorks. The variation of temperature transfer inside the propellant charge was simulated by ANSYS finite element simulation software, and the relationship between the temperature distribution of the propellant charge and the holding time was obtained. Preservation of the time required. The result proves that the current military standard stipulates that the heat preservation time does have a lot of compression space.