| 某型号发动机可燃点火器的设计 |
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| 引用本文： | 毛思迁,屠小昌,胡大宁. 某型号发动机可燃点火器的设计[J]. 航空兵器, 2010, 0(2): 32-34 |
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| 作者姓名： | 毛思迁 屠小昌 胡大宁 |
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| 作者单位： | 航天科工集团二院210所,西安,710065;驻天水地区军事代表室,陕西,宝鸡,721006 |
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| 摘 要： | 以某型号发动机为背景,设计了一种可燃点火器,由可燃发火管、可燃壳体、点火药、堵头等组成。经过模拟点火试验和发动机地面静止试验,证实该点火器能够满足发动机的技术指标要求。
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| 关 键 词： | 固体火箭发动机 可燃点火器 |
Combustible Igniter Design for a Certain Model of Solid Propellant Rocket Motor |
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| MAO Si-qian,TU Xiao-chang,Hu Daning. Combustible Igniter Design for a Certain Model of Solid Propellant Rocket Motor[J]. Aero Weaponry, 2010, 0(2): 32-34 |
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| Authors: | MAO Si-qian TU Xiao-chang Hu Daning |
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| Affiliation: | 1. No. 210 Institute of the Second Academy of CASIC, Xi＇ an 710065 ,China; 2. The Representative of Ordnance Equipment Management in Tianshui Area, Baoji 721006, China) |
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| Abstract: | A combustible igniter is designed in the background of a certain model of solid propellant rocket motor, which consists of the combustible initiator, combustible tube, ignition composition, plug, etc. The simulation tests and ignition of solid propellant rocket motor staticground tests show that the combustibe igniter meets the technical requirement of the motor. |
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| Keywords: | solid propellant rocket motor combustible igniter |
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