Abstract: In order to study the ablation of aircraft and the thermal protection of its shell materials when reentry into the atmosphere, a 5kW level plasma generator was designed for the stagnation ablation test in small plasma wind tunnel based on the ground test of reentry. The power, cathode structure and anode structure of the plasma generator are analyzed and designed in detail. Adopting the magnetohydrodynamic model with the local thermodynamic equilibrium, the effects of current including 90A, 100A, 110A and 120A on the plasma generator were simulated and analyzed. A preliminary ignition test was carried out using laboratory vacuum system and power supply equipment to verify the basic performance of the plasma generator. The results show that, compared with the simulation results, the discharge voltage error of the designed working medium is 8%, and that of the ignition test is 6.25%. So the simulation model of plasma generator is reliable, the designed plasma generator meets the expectation and works normally. It provides an important reference for the subsequent stagnation ablation test.

Key words: Ground test of reentry;Plasma generator;Simulation;Ground test

摘要： 为了研究再入大气层时，飞行器所遭受的烧蚀情况和其外壳材料的热防护作用，围绕地面模拟再入环境的小型等离子体风洞系统，从等离子体发生器的功率计算和阴极、阳极结构参数入手，设计了用于驻点烧蚀试验的5kW级别小功率等离子体发生器。采用局域热力学平衡的方法，选择工作电流分别为90A，100A，110A和120A，对等离子体发生器性能的影响进行了研究。利用实验室真空系统与电源设备，开展初步点火试验，验证了等离子体发生器的基本性能。结果表明：与仿真计算结果相比，设计状态工质下的放电电压误差为8%，点火试验测得的放电电压误差为6.25%，参数对比验证了等离子体发生器仿真模型计算可靠，设计的等离子体发生器符合预期，工作正常。

关键词: 地面模拟再入;等离子体发生器;仿真计算;地面试验