粉末火箭发动机推力调节试验研究  

Experimental investigation on thrust regulation of powdered rocket motor

作　　者：张胜敏[1] 杨玉新[1] 胡春波[2] 

机构地区：[1]中国航天科技集团公司四院四十一所,西安710025 [2]西北工业大学,西安710072

出　　处：《固体火箭技术》2015年第3期347-350,共4页Journal of Solid Rocket Technology

摘　　要：为了验证粉末火箭发动机的多次点火启动及推力调节等技术,利用设计的发动机开展了试验研究。研究结果表明,在高能火花塞作用下,粉末火箭发动机可实现多次点火启动及关机,且启动及关机的次数、时间间隔等可随意调节;通过调节粉末燃料和氧化剂的流量,可实现粉末火箭发动机的推力调节技术,推力调节比达到6.5。An experiment system of powdered rocket motor was established to investigate some key technologies, such as multiple startups and thrust regulation and so on, large numbers of experiments were conducted. The results indicat that under the effect of high energy spark plug,powered rocket motor can realize multiple startups and shutdown.Moreover startup and shutdown times, the time intervals can be regulated randomly. By adjusting the flow rate of the powder fuel and oxidant, powered rocket motor can a-chieve thrust control technology,and thrust regulation ratio reaches 6.5.

关 键 词：粉末火箭发动机 试验研究 推力调节 点火 关机 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]