微型固体火箭发动机用短点火延迟点火器研究

推进技术 ›› 1995, Vol. 16 ›› Issue (3): 42-45.

微型固体火箭发动机用短点火延迟点火器研究

范存杰,李逢春

西北工业大学航天工程学院;西北工业大学航天工程学院

发布日期:2021-08-15

A STUDY ON IGNITER TO SHORTEN IGNITION DELAY TIME FOR MICRO-SOLID PROPELLANTS ROCKET MOTOR

College of Astronautics, Northwestern Polytechnical University, Xi’an, 710072;College of Astronautics, Northwestern Polytechnical University, Xi’an, 710072

Published:2021-08-15

摘要/Abstract

摘要： 短的点火延迟或对某些微型固体火箭发动机尤为重要。文中引用固相点火理论，在诸多向推进剂表面供热的方式中，着重分析了起重要作用的对流换热。认为提高点火燃气的流速能明显地提高点火燃气对推进剂表面的热交换率，使推进剂表面很快达到发火温度。在微型固体火箭发动机的短点火延迟时间点火器设计中应用了这一理论，并获得了理想的效果。

关键词: 微型火箭发动机;点火延迟;点火器;传热

Abstract: he shortened ignitoin delay time is extremely important for some microsolid propellant rocket motors. In this paper, solid-state ignition theory and ignition course of hot gases are used. The study verifies that high flow rate of ignition gases rises heat exchange of gases to the propellants grain surface and the ignition temperature is reached rapidly. The theory is applied to igniter designs to shorten ignition delay time,and to obtain perfect igniter for micro-solid propellants rocket motors.

Key words: Microrocket engine;Ignition delay;Igniter;Heat transfer

范存杰,李逢春. 微型固体火箭发动机用短点火延迟点火器研究[J]. 推进技术, 1995, 16(3): 42-45.