摘要
为快速准确揭示固体燃料冲压发动机性能,提出一种在燃烧室考虑热力计算的性能计算模型。通过查找进气道中正激波位置,进行了进气道、燃烧室、喷管耦合计算。并以VB为平台,开发出通用的发动机性能计算软件。以一种固体燃料冲压增程弹为例,计算结果与实验数据进行了对比,表明该方法可快速的预示发动机整体性能,缩短设计周期,能够满足方案设计阶段的精度要求。
In order to reveal the performance of solid fuel ramjet （SFRJ） quickly and accurately, a model with thermal calculation in the chamber was presented. By calculating the position of normal shock in the inlet, the performance of the inlet, combustor and nozzle was obtained with coupled method. Based on VB, the universal software for the engine performance calculation was developed. A model of solid fuel ramjet extended-range projectile was employed and the calculation results agreed well with experimental data. The results indicate that the engine performance can be rapidly predicted with this method, thus to reduce design period and satisfy the precision demand in the schematic design.
出处
《弹箭与制导学报》
CSCD
北大核心
2013年第2期79-81,共3页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
固体燃料冲压增程炮弹
组分
推力
比冲
solid fuel ramjet extended-range projectile
species
thrust
specific impulse
