根据膏体推进剂火箭发动机点火的要求，提出了复合等离子点火的方案，针对等离子点火的特点，采用电晕和电弧双等离子复合工作模式，研制了一套等离子点火系统，并进行了相应的点火试验.结果表明，该方案点火系统引弧率高、功率大、可靠性好，复合等离子点火时间较常规的点火药点火时间长，不会出现火药点火中的初始压力峰值，可以满足膏体推进剂火箭发动机多次点火的要求，达到了设计的最初目的.
Abstract
According to the requirement of pasty propellant rocket motor, a composite plasma igniting plan was adopted. Aiming at the characteristics of plasma ignition, a set of plasma igniting system was developed by composite operation mode of double plasma of electric corona and electric arc, and some ignition tests were done. Experimental results show that this ignition system has such advantages as big power, high reliability and etc. The firing time of composite plasma is longer than that conventional igniter pad. There is no initial pressure peak in the composite plasma igniting system. The plan fit the demand of multiple ignition of pasty propellant rocket motor. The purpose of design was attained.
关键词
火箭发动机 /
膏体推进剂 /
等离子点火
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Key words
rocket motor /
pasty propellant /
plasma ignition
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参考文献
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脚注
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