摘要
介绍一种低功率电弧加热发动机系统的实验研究。该系统包括电源,点火系统,推进剂供给系统,发动机本体和一些测量设备。用氮和氩对不同的喷口喉道直径(0.6mm~1mm),不同的质量流率(20mg/s~100mg/s),不同的电源电压(80V~150V)进行了性能研究。所有试验都是在直径为1m,长为1.
A laboratory system of low power(1 kW class)arcjet engine is described.It consists of a power supply and ignition system,propellant feeding system,engine body and some measurment devices. The performances described were acquired for different constrictor diameters(0 6~1 mm),mass flow rates(20~100 mg/s)and voltages(80~150 V)of power supply with Nitrogen and Argon.All of the tests were conducted in a 1 6 m long and 1 m in diameter vacuum chamber.
出处
《中国空间科学技术》
EI
CSCD
北大核心
1997年第4期41-48,共8页
Chinese Space Science and Technology
关键词
卫星控制
等离子体推进
电弧加热发动机
Satellite control Engine Plasma propulsion Arc heating Experimentation