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介绍了一种新型微型固体火箭的结构特点。首次通过微弧氧化工艺实现了铝合金材料在制造微型固体火箭燃烧室壳体方面的应用,并经数值计算验证微弧氧化层的隔热效果。根据微型固体火箭结构特点选用了半导体桥作为点火装置。为了进一步研究微型固体火箭族在空间中分组点火工作状况,设计了模拟微型固体火箭族(实验设计为180个)空间点火的实验台。实验台实现了通过小型键盘输入火箭代号,同时LED显示器显示以及单片机控制半导体桥点火等工作过程。
The structural characteristics of a new type of miniature solid rocket are introduced. For the first time, the application of aluminum alloy material in manufacturing micro-solid rocket combustion chamber shell was realized by micro-arc oxidation process, and the thermal insulation effect of micro-arc oxidation layer was verified by numerical calculation. According to the characteristics of micro-solid rocket structure selected semiconductor bridge as the ignition device. In order to further study the working status of micro-solid rocket family in group space ignition, a test bench for simulating the micro-solid rocket family (180 experimental designs) was designed. Test bench to achieve the rocket code through a small keyboard, while the LED display and microcontroller control semiconductor bridge ignition and other work processes.