论文部分内容阅读
为了更加合理有效地设计轨道冷却系统,对轨道温度进行了实验测量及仿真计算。搭建电磁发射实验及轨道温度测量系统,利用热电偶对电磁发射过程进行轨道温度的实际测量,在线获得轨道瞬态温度。在此基础上,基于Comsol Multiphysics平台,利用有限元方法,建立轨道横截面二维模型,对发射中轨道温升这一瞬态过程进行仿真计算,在电磁场与温度场耦合的情况下,求解轨道横截面的电流与温度分布。结果显示:轨道尾部的温度高于出口处,电枢起始位置附近温升最高;轨道温度在焦耳热的作用下逐渐升高,高温集中在轨道内表面。根据实验和仿真的温度分布结果,可以更加合理地设计轨道冷却系统。
In order to design the orbital cooling system more reasonably and effectively, experimental measurements and simulation calculations of the orbital temperature were carried out. Set up electromagnetic emission experiment and track temperature measurement system, the use of thermocouple on the electromagnetic emission process of the actual measurement of orbital temperature, orbital transient temperature. On this basis, based on the Comsol Multiphysics platform, the finite element method is used to establish a two-dimensional cross-section model of the track to simulate the transient process of orbital temperature rise during the launch. When the electromagnetic field is coupled with the temperature field, the orbit Cross section current and temperature distribution. The results show that the temperature at the tail of the track is higher than that at the exit and the temperature rise is highest near the beginning of the armature. The orbital temperature is gradually increased under the action of Joule heat, and the high temperature is concentrated on the inner surface of the track. Based on the experimental and simulation results of temperature distribution, the orbital cooling system can be designed more reasonably.