amorce

Taking aft-end igniter design for a rocket motor for example, design methods for ignition sequence, amorce quantity estimation and nozzle closure were described respectively.

以某型号发动机尾部点火设计为研究对象，对点火序列设计、点火药量的估算、喷管堵片的设计方法进行了阐述。

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Method of amorce mass estimation for solid rocket motor

固体火箭发动机的一种点火药量估算方法

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The results indicated that, though the amorce mass was the same, the ignition pressure, the ignition delay and opened manner of the nozzle closure were different.

结果表明，虽然点火药量相同，但两种点火方案的点火压强、点火延迟时间、喷管堵片的打开方式却存在较大差异。

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Ignition pressure can be improved gradually and some technology problems such as ignition delay and ignition failure at the preliminary stage were solved by adjusting amorce quantity and nozzle closure design state.

通过调整点火药量、喷管堵片设计状态，使点火压强逐步提高，解决了发动机研制初期出现的点火延迟、不点火等技术问题。

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Based on the experimental formula of fore-ignition design, the initial amorce mass of a small solid rocket motor with end-and-lateral burning grain and aft-ignition manner was estimated firstly.

采用头部点火设计经验公式对端面-侧面燃烧、尾部点火的小型固体火箭发动机点火药量进行了初步估算。

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