摘要
提出了一种能计算二维火箭喷焰流场化学组份和电磁特性分布的计算模型和方法,并编制了相应的计算机程序。该程序能较真实地反映喷焰流场中发生的实际化学反应和电磁波衰减效应,适用于接近完全膨胀的少烟或无烟推进剂火箭喷焰参数的计算。计算结果表明,不考虑化学反应,将对流场内参量,特别是化学参量和电磁参量的计算结果产生很大误差。
A computational modeling technique and prediction method are presented for calculating two-dimensional profiles of chemical species mole fraction and electrical properties of rocket exhaust plumes. A comprehensive computer code has been programmed. The chemical reactions and radar attenuation which occur.in a rocket plume can be predicted more truly by using this code. It is suitable to calculating parameters of rocket plumes under a near complete-expansion condition and for smokeless (or reduced smoke) propellant apply-cation. The calculation results indicate that evident errors will occur for prediction of chemical and electrical parameters in the plume flowfield if the chemical reactions in the plume are ignored.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1993年第4期8-13,共6页
Journal of Propulsion Technology
基金
国家科研课题鉴定成果之一
关键词
火箭发动机
排气火焰
流场
计算
Rocket engine, Exhaust flame, Flow field, Chemical composition, Electromagnetic property, Calculation method
