The structure of the solid propellant micro-thruster is simple,the energy density of the solid propellant micro-thruster is high,and the working property of the solid propellant micro-thruster is stable.Theses characteristics are beneficial to the integration of systems.The expected thrust and impulse of the thruster can be obtained by setting the structure and size of the micro thruster and the composition and content of the propellant.So the solid propellant micro-thruster is especially suitable for micro spacecraft to meet the needs of military and civil.However,the chamber of the micro-thruster is small,so the heat loss caused by the larger surface area and the microscale effect are high.Furthermore,the successful,quick ignition and sustained,steady and intense,efficient combustion of fuels in it are difficult,and that is the importance of the study.The structure type,ignition devices,material selection,propellant formulation and test systems,of the solid propellant micro-thruster are summarized,and the development direction is proposed.Boron is considered to be an attractive high-energy metallic fuel for use as the fuel-rich solid propellant because of its high gravimetric and volumetric caloric value during combustion.Therefore,the boron-based propellant as the energy element is selected,and its law of performance and improvement measures is studied.The direction for the optimization of the boron-based propellant formulation and the structure size of the micro thruster will be showed.%总结了固体推进剂微推进器的结构类型、点火装置、材料选择、推进剂配方、测试系统等,并提出未来的发展方向.而硼的质量热值和体积热值大,是火箭冲压发动机固体推进剂的首选燃料.分析含硼推进剂作为微推进器的能量单元,研究其性能规律及改进措施,将为含硼推进剂配方优化和微推进器结构尺寸优化指明方向.
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