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为了掌握轨道电磁发射中电枢的电流熔蚀特性,对小口径电磁轨道发射装置进行了实验研究。实验装置为20 mm×20 mm,方形口径轨道电磁发射装置,通过控制发射实验中电枢出膛的速度,研究了电流幅值、电枢质量和转角厚度(载流能力)等因素对熔蚀的贡献。另外,基于电流幅值递增实验,总结了熔蚀程度的几种模型和相应的电流幅值范围。结果表明:不同的发射条件对电枢的熔蚀程度影响有所差异;电流分布是熔蚀产生的直接原因,能显著影响熔蚀程度;电枢质量对起始时刻的熔蚀有影响;电枢转角厚度对熔蚀的贡献不大(电枢载流能力足够的情况下);随着电流幅值的增加,电枢表面熔蚀有从电枢中端偏下位置沿棱边向电枢中部和电枢头部延伸的趋势,在此过程中归纳出了3种熔蚀程度及其对应电流范围:轻度熔蚀,对应电流181~293.8 k A;中度熔蚀,对应电流293.8~320.8 k A;极度熔蚀,电流>320.8 k A。
In order to grasp the current corrosion characteristics of the armature in orbit electromagnetic launch, an experimental study on a small-aperture electromagnetic orbit launcher was carried out. The experimental device is a 20 mm × 20 mm square orbital electromagnetic transmitter. By controlling the speed of the armature chamber in launching experiments, the effect of current amplitude, armature mass and corner thickness (current carrying capacity) Contributions. In addition, based on the current amplitude increment experiment, several models of the degree of erosion and the corresponding current amplitude range are summarized. The results show that the influence of different emission conditions on the degree of corrosion of the armature is different. The current distribution is the direct cause of the corrosion and can significantly affect the degree of corrosion. The quality of the armature has an influence on the initial erosion. The thickness of the pivot angle contributes little to the corrosion (with sufficient armature current carrying capacity); with the increase of the current amplitude, the armature surface has the corrosion along the edge from the lower end of the armature to the armature In this process, three kinds of degree of erosion and their corresponding current ranges are summarized: slight erosion, corresponding current of 181-293.8 kA; moderate erosion, corresponding current of 293.8 ~ 320.8 kA; Extremely corrosive, current> 320.8 kA.