固体火箭超燃冲压发动机理论性能分析

doi:10.7527/S1000-6893.2022.26971

Abstract

Abstract:

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.

Key words: solid rocket scramjet, high Mach number, dissociation, engine performance, solid propellant

CLC Number:

V435

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.

Figures/Tables 21

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燃烧室处理方法	不考虑离解	化学平衡
来流静温/K	226.65	226.65
隔离段出口静温/K	1 511.2	1 511.2
燃烧室静温/K	2 651.7	2 429.0
来流总温/K	3 124.9	3 124.9
燃烧室总温/K	4 265.4	3 557.7

数据来源	获取方式	P₃/kPa	P₄/kPa
文献［21］	飞行试验测量	≈57	57~120
计算	等压燃烧	57	57
计算	气流速度恒定	57	85

试验	工况	数据来源	P₃/kPa	U₃/（m·s^-1）	T₃/K	Ma₄	P₄/kPa
飞行试验	H=32.5 km， Ma=7.7	文献［21］	≈57	≈1 800	≈1 500		57~120
	H=32.5 km， Ma=7.7	计算	57	1 718	1 423	1.73	85
	H=27.1 km， Ma=7.8	文献［21］	≈130	≈1 720	≈1 300
	H=27.1 km， Ma=7.8	计算	140	1 685	1 444	1.74	194
HEG XII	H=33.0 km， Ma=7.3	文献［21］	57	1 800	1 500	1.0~2.3	57~145
HEG XII	H=33.0 km， Ma=7.3	计算	47	1 632	1 313	1.63	76
HEG XIII	H=28.0 km， Ma=7.4	文献［21］	130	1 720	1 300	1.65~2.30	130~280
HEG XIII	H=28.0 km， Ma=7.4	计算	106	1 606	1 327	1.70	152

A/F	摩尔占比
A/F	CO	CO₂	H	H₂	H₂O	NO	N₂	O	OH	O₂
5	0.26	0	0	0.25	0	0	0.49	0	0	0
10	0.12	0.06	0	0.04	0.12	0	0.66	0	0	0
15	0.03	0.10	0	0	0.11	0.01	0.72	0	0.01	0.02

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Theoretical analysis of performance of solid rocket scramjet

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