微型续航固体火箭发动机设计及试验方法研究

A Study on Design and Test Method for Solid Propellant Endurance Micro-rocket

介绍了毫米级固体推进剂火箭发动机的设计和试验方法，并将其用作一次性的执行微型传感器网络节点系统的展开平台．此火箭发动机由燃烧室、推进剂燃料、喷管、点火器组成．点火器采用电点火方式．对微型化后需解决的火箭设计问题进行了讨论，提出了相应的设计原则和方法．用这种方法设计的火箭质量仅为2g，比冲在230860N·s／kg范围内，测量到的推力达到24～230mN．

The design and test of millimeter-scale solid propellant micro-rocket was studied. It was applied to disposable deployment platform for carrying communication equipped MEMS sensor network node system. This kind of micro-rocket engine consists of a combustion chamber, propellant grain, nozzle and igniter. The ignite type of the igniter is electric ignition. Some problems about mlcro-rocket design were discussed. The relative design principle and methods were proposed. Up to 24-230 mN thrust has been measured for this kind miniaturization of solid propellant micro-rocket weighing under 2 g, with specific impulse of 230-860 N·s/kg range.