The digital micro-propulsion system based on the solid propellant sequentially comprises a spray pipe layer, a combustion chamber and an ignition circuit layer from top to bottom. The ignition circuit layer, the combustion chamber layer and the spray pipe layer respectively and independently comprise a spray pipe unit, a combustion chamber unit and an ignition unit which are in a planar array form; the ignition units, the combustion chamber units and the spray pipe units on the same array point are sequentially connected in the longitudinal direction and correspond in position. Wherein the combustion chamber unit comprises a solid propellant located at the lower end, an afterburning chamber located at the upper end and a lining located between the wall body of the combustion chamber unit and the solid propellant; the top of the afterburning chamber is connected with an inlet of the nozzle unit; the ignition unit is connected with the bottom of the solid propellant. Through the design of an array structure formed by the spray pipe unit, the combustion chamber unit and the ignition unit, wide-range and high-precision adjustment in the thrust aspect can be achieved by controlling array number work.
提供了一种基于固体推进剂的数字式微推进系统,从顶部到底部依次包括喷管层、燃烧室、点火电路层;点火电路层、燃烧室层和喷管层分别各自独立地包括平面阵列形式的喷管单元、燃烧室单元和点火单元;同一阵列点上的点火单元、燃烧室单元和喷管单元在纵向依次连接且位置对应;其中燃烧室单元包括位于下端的固体推进剂、位于上端的补燃室和位于燃烧室单元壁体与固体推进剂之间的衬层;补燃室顶部连接喷管单元的入口;点火单元与固体推进剂底部连接。本发明通过喷管单元、燃烧室单元和点火单元形成的阵列结构设计,可通过控制阵列数工作实现在推力方面宽范围、高精度可调。
Digital micro-propulsion system based on solid propellant
一种基于固体推进剂的数字式微推进系统
2024-05-03
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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