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阴极热子组件作为星载行波管的电子注源,要求它具备优良的热、力特性,以满足星载行波管高效率、高可靠、长寿命的需求。本文利用ANSYS有限元软件对星载行波管阴极热子组件结构进行了热模拟,并完成了热测实验,实验结果表明,阴极温度计算精度在5%以内,结构整体的温度计算误差在72℃以内,验证了热模型的可靠性。进一步的,理论研究并数值模拟了阴极支持筒开槽方案及关键开槽参量对结构热效率和力学可靠性的影响,提出了开槽方案的设计方法。最后,对现结构开槽方案进行了优化设计,模拟结果表明,优化后的阴极热子组件结构热效率提高了15.2%,同时结构满足力学试验的要求。
The cathode thermal subassembly, as an electron injection source of spaceborne traveling wave tube, requires excellent thermal and force characteristics to meet the requirements of high efficiency, high reliability and long life of spaceborne traveling wave tube. In this paper, ANSYS finite element software was used to simulate the structure of the TTG cathode thermal subassembly, and the thermal test was completed. The experimental results show that the calculation accuracy of the cathode temperature is within 5% and the temperature error of the whole structure is 72 ℃, verify the reliability of the thermal model. Further, the theoretical study and numerical simulation of the effect of the slot support scheme of the cathode support cylinder and the key slotted parameters on the thermal efficiency and mechanical reliability of the structure are presented. The design method of the slotted scheme is proposed. Finally, the slotted scheme of the present structure is optimized. The simulation results show that the thermal efficiency of the optimized structure of the cathode thermal subassembly is improved by 15.2% and the structure meets the requirements of the mechanical test.