固体火箭发动机羽焰测温方法研究  

A Study on Measurement Method of Exhaust Flames Temperature for Solid Propellant Rocket Engine

作　　者：范传新[1] 王鹏[1] 

机构地区：[1]中国航天科技集团公司四院四十四所,西安710025

出　　处：《宇航计测技术》2006年第4期18-22,共5页Journal of Astronautic Metrology and Measurement

摘　　要：根据固体火箭发动机羽焰特征研制了多目标多光谱高温仪,它可同时测量羽焰六个目标点的温度,每个目标点均有八个工作波长。同时提出了求解真温的实用方法,完成了固体火箭发动机羽焰温度及其分布的测量。The multiple target multi-spectral pyrometer based on the exhaust flames characteristics of solid propellant rocket engine（SPRE） is developed for measuring simultaneously the exhaust flames temperature of six targets with eight working wavelengths for each target. An applicable effective true temperature solving method is presented. The measurement of SPRE exhaust flames temperature and its distribution is completed with multi-spectral pyrometer.

关 键 词：排气火焰 光谱测温仪 固体推进剂火箭发动机 动态测量 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]