基于布雷顿循环，考虑燃烧产物的离解，针对固体火箭超燃冲压发动机工作过程进行了建模研究，开展了发动机理论性能分析，研究了飞行参数、燃料种类对发动机性能的影响，探究了超燃冲压发动机的工作极限。结果表明：固体火箭超燃冲压发动机的性能随着飞行马赫数的增大和飞行高度的升高而下降；当工作当量比增大时，质量比冲和体积比冲均下降，但比推力逐步上升；当工作空燃比增大时，比推力下降，但质量比冲和体积比冲均逐步升高。燃料种类对发动机性能有显著影响，在空燃比5~27的范围内，固体推进剂的体积比冲存在明显优势，但比推力和质量比冲不及氢气和煤油。相比于氢气和煤油，采用硼基固体推进剂作为燃料的超燃冲压发动机可以在更宽的飞行马赫数范围内工作，预示着固体火箭超燃冲压发动机宽包络飞行的潜力。

Considering the dissociation of combustion products， this paper conducts research on modeling of the working process of the solid rocket scramjet using the Brayton cycle method. Then， the theoretical performance of the engine is analyzed， and the effects of flight parameters and fuel types on engine performance are studied. The flight envelope of scramjet engine is also discussed. The main conclusions are as follows. The performance of solid rocket scramjet decreases with the increase of flight Mach number and flight altitude. When the working equivalent ratio increases， the gravimetric impulse and volumetric impulse decrease， but the specific thrust increases gradually. When the working air-fuel ratio increases， the specific thrust decreases， but the gravimetric impulse and volumetric impulse increase gradually. In the range of air-fuel ratio from 5 to 27， the volumetric impulse of the engine fueled with solid propellant has obvious advantages， but the specific thrust and gravimetric impulse are inferior to the engine fueled with hydrogen and kerosene. Compared with that fueled with hydrogen and kerosene， the boron-based solid propellant scramjet can work in a wider range of Mach numbers， which indicates that the solid rocket scramjet has a potential of wide flight envelope.