The invention relates to the technical field of spaceflight, in particular to a low-impact large-ratio-burst-open parachute firer device which comprises an igniter, a combustion chamber assembly, an ignition assembly and a main charging assembly. The combustion chamber assembly comprises a front sealing head, a spraying pipe, a blanking cap and a combustion chamber shell; a plurality of spray pipe mounting holes are uniformly distributed in the side surface of the front sealing head; the spray pipe is fixedly and hermetically connected with the spray pipe mounting hole, and the spray pipe is communicated with the cavity of the front sealing head; the blanking cap is located in the spray pipe and plugs the spray pipe; the front end of the combustion chamber shell is communicated with the cavity of the front sealing head, and the rear end of the combustion chamber shell is connected with the ignition assembly; the main charging assembly is located in the combustion chamber shell and comprises a plurality of main charging columns. A closed space is defined by the ignition assembly, the front end socket and the combustion chamber shell. The igniter ignites ignition powder in the ignition assembly, the ignition powder combusts to ignite the main charging column, generated high-temperature and high-pressure fuel gas is ejected out in an accelerated mode through expansion of the spray pipe, thrust is generated, and parachute opening can be rapidly and effectively achieved. And the firer device is safer and more reliable.
本发明涉及航天技术领域,尤其涉及一种低冲击大比冲开伞火工装置,包括点火器、燃烧室组件、点火组件和主装药组件;燃烧室组件包括前封头、喷管、堵盖、燃烧室壳体;前封头内具有腔体,其侧面均布多个喷管安装孔;喷管与喷管安装孔固定、密封连接,且喷管与前封头的腔体连通;堵盖位于喷管内,将喷管封堵;燃烧室壳体为筒状,前端与前封头的腔体连通,后端连接点火组件;主装药组件位于燃烧室壳体内,主装药组件包括多根主装药柱;点火组件、前封头和燃烧室壳体围成封闭空间;点火器点燃点火组件内的点火药,点火药燃烧点燃主装药柱,产生的高温高压燃气通过喷管膨胀加速喷出,产生推力,能够快速、有效的实现开伞;火工装置更加安全、可靠。
Low-impact large-specific-impact parachute-opening firer device
一种低冲击大比冲开伞火工装置
2023-04-18
Patent
Elektronische Ressource
Chinesisch
IPC: | B64G Raumfahrt , COSMONAUTICS |
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