固体火箭冲压发动机设计点性能优化分析

Optimal analysis of design point performance of ducted rocket

针对冲压动力飞行器射程优化总体需求,提出了基于飞行器-发动机性能因子的评估方法,建立了固体火箭冲压发动机性能模型及优化设计流程,为总体与动力一体化优化设计提供了支撑。根据典型含硼贫氧推进剂性能分析结果可知,相同马赫数及余气系数下,高度对比冲的影响不明显;相同马赫数下,比冲随余气系数的增加先增加后减小;相同余气系数下,比冲随马赫数的增加而降低;飞发性能因子随马赫数、余气系数的增加先增加后降低,在一定条件下达到最大值。

Aimed at range optimization requirements of vehicle with ramjet,an evaluation method based on the vehicle-ramjet performance factor is proposed.Performance prediction model and optimization design process of ducted rocket are developed.These provide support for the integrated optimization design of vehicle and ramjet.According to the analysis results of ramjet performance with boron-based fuel rich propellant,under the same Mach number and excess air coefficient,the change of specific impulse caused by height variation is not obvious.Under the same Mach number,the specific impulse increases first and then decreases with the increase of excess air coefficient.Under the same excess air coefficient,the specific impulse decreases with the increase of Mach number.With the increase of the Mach number and excess air coefficient,vehicle-ramjet performance factor increases first and then decreases.The vehicle-ramjet performance factor reaches a maximum under certain Mach number and excess air coefficient.