Application of high burning rate propellant to impulsive microthruster

被引：0

作者：

Li, SP ^{[1
]}

Zhang, P ^{[1
]}

机构：

[1] Beijing Inst Technol, Sch Mech Elect Engn, Beijing 100081, Peoples R China

来源：

THEORY AND PRACTICE OF ENERGETIC MATERIALS, VOL 5, PARTS A AND B | 2003年

关键词：

solid propellant; impulsive microthruster; high burning rate; ignition;

D O I：

暂无

中图分类号：

O414.1 [热力学];

学科分类号：

摘要：

To explore the application capability of high burning rate solid propellant available in China to the attitude control of hypervelocity flight vehicle, some exploratory test has been conducted and the two application examples of it are discussed.. The reason of the application of high burning rate propellant to an impulsive microthrusters is also introduced. It is shown from tests that even if the propellant burning rate is not high enough, the demand of burning time within 10ms can be still satisfied if the appropriate grain design technology are adopted; and the math performance of igniter and propellant grain is the keypoint of getting the satisfied internal ballistics of an impulsive microthruster.

引用

页码：620 / 623

页数：4