固冲发动机设计点性能迭代计算(英文)

Iterative calculations for solid rocket ramjet performances on design condition

固冲发动机热力学性能参数计算是发动机性能计算的重要部分,通常是针对特定的推进剂建立热力学数据表格,然后通过插值取得相应参数。通过对NASA CEA程序进行二次开发,使其成为便于应用的子程序,并以补燃室热力计算为基础,通过给定推进剂配方、进气道总压恢复系数、补燃室燃烧效率、比冲效率等设计参数,建立了满足总体推力要求的固冲发动机设计点性能迭代计算方法,为固冲发动机方案设计提供了一种实用工具。

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.