Iterative calculations for solid rocket ramjet performances on design condition

Dong Xing Huo, Guo Qiang He, Lin Quan Chen, Yan Fang Li

Research output: Contribution to journalArticlepeer-review

1 Scopus citations

Abstract

Thermodynamic parameters calculations are one of the important parts for solid rocket ramjet(SRR) performance analysis. Commonly, the parameters are obtained by means of interpolation from data tables which is established for specified propellant. NASA CEA program is secondary-developed successfully to a subroutine. Based on the afterburner thermodynamic calculations, the iterative algorithm for solid rocket ramjet performance on design point is investigated. The propellant composition, air inlet total pressure recovery coefficient, combustion efficiency, and nozzle impulse efficiency are assumed according to experiment. The iterative algorithm is an utility software for SRR scheme design.

Original languageEnglish
Pages (from-to)401-405
Number of pages5
JournalGuti Huojian Jishu/Journal of Solid Rocket Technology
Volume33
Issue number4
StatePublished - Aug 2010

Keywords

  • Design condition
  • Performance calculation
  • Solid rocket ramjet
  • Thermodynamic analysis

Fingerprint

Dive into the research topics of 'Iterative calculations for solid rocket ramjet performances on design condition'. Together they form a unique fingerprint.

Cite this