ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Theoretical analysis of performance of solid rocket scramjet
Received date: 2022-01-19
Revised date: 2022-02-10
Accepted date: 2022-02-24
Online published: 2022-03-22
Supported by
National Natural Science Foundation of China(52006240);Natural Science Foundation of Hunan Province(2020JJ4665)
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.
Xiang ZHAO , Zhixun XIA , Chuanbo FANG , Likun MA , Chaolong LI , Yifan DUAN . Theoretical analysis of performance of solid rocket scramjet[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023 , 44(5) : 126971 -126971 . DOI: 10.7527/S1000-6893.2022.26971
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