节流式燃/氧分离发动机准一维内弹道数值研究

doi:10.7527/S1000-6893.2023.29111

Abstract

Abstract:

A predictive unsteady quasi-one-dimensional internal ballistic numerical model and a set of performance regulation mechanism formulas are established for throttling segregated fuel-oxidizer systems. The numerical model considers combustion gas injection， wall friction， and propellant surface regression， using a finite-rate chemical reaction model to describe the non-equilibrium process. With this model， performance parameters and internal flow parameter distributions of the throttling segregated fuel-oxidizer system can be well demonstrated.Results show that， adjustment of the throat radius of the throttle valve from 2.89 mm to 1.65 mm increases the thrust of the system from 105.09 N to 432.18 N， by 411.25% from the original thrust， verifying the regulation capability of the throttling segregated fuel-oxidizer system. During the dynamic operation of the throttle valve， the system experiences anti-regulations. Faster actuation of the valve leads to larger anti-regulation amplitude and shorter response period of the performance parameters. Analysis of the influencing factors of performance regulation reveals that the increase of propellant pressure index and the decrease of nozzle throat radius both contribute to the improvement in performance regulation ability of the throttling segregated fuel-oxidizer system. Accordingly， a new arrangement of throttling segregated fuel-oxidizer system with an adjustable nozzle is proposed. Simulation of this arrangement suggests that， for a specified thrust adjustment ratio， reducing the nozzle throat radius can effectively alleviate the pressure level of the fuel-rich combustion chamber of the system， thus providing more feasible performance regulation schemes for the system operation.

Key words: solid rocket motor, segregated fuel-oxidizer system, quasi-one-dimensional internal ballistics, thrust regulation, performance regulation mechanism

CLC Number:

V438.2

Ge WANG, Zhibang WANG, Fuqi WANG, Ben GUAN, Limin WANG, Haoran NING. Numerical study on quasi⁃one⁃dimensional internal ballistics of throttling segregated fuel⁃oxidizer systems[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(7): 129111-129111.

Figures/Tables 21

Table 1

Values of burning rate a* coefficients and pressure index n of fuel⁃rich and oxygen⁃rich propellants

p /MPa	富燃推进剂^［29］		富氧推进剂^［30］
p /MPa	$a *$	n	$a *$	n
0~2	6.11	0.88	5.10	0.67
2~4	8.76	0.34	5.10	0.67
>4	5.97	0.63	5.10	0.67

Table 1

Table 2

Fig.1

Table 3

Fig.2

Fig.3

Table 4

Fig.4

Fig.5

Fig.6

Fig.7

Fig.8

Table 5

Performance parameters of throttling SFOS with different throttle valve throat radii

R/mm	p_f /MPa	p_o/MPa	$m ˙ f$ /（g·s^-1）	$m ˙ o$ /（g·s^-1）	$m ˙ f / m ˙ o$	I_sp/（m·s^-1）	F/N
2.89	1.00	0.90	20.59	30.12	0.68	2 072.32	105.09
2.84	1.03	0.92	21.28	30.54	0.70	2 071.49	107.35
1.90	8.90	2.41	81.84	58.81	1.39	2 028.39	285.29
1.65	20.00	3.64	136.59	78.26	1.75	2 011.53	432.18

Table 5

Fig.9

Fig.10

Fig.11

Fig.12

Fig.13

Table 6

Internal ballistic parameters before and after motor performance regulation with different A¯t/At （N=4.00）

$A ¯ t / A t$	$m ˙ f / m ˙ o$	$m ˙ ¯ f / m ˙ f$	$m ˙ ¯ f / m ˙ ¯ o$	$p ¯ f / p f$	$p ¯ o / p o$
1.00	0.20	11.34	0.90	48.99	4.00
1.00	0.70	6.10	1.69	18.29	4.00
1.00	1.50	4.98	2.95	13.26	4.00
1.00	4.00	4.37	6.90	10.77	4.00
0.80	0.20	9.30	0.63	35.76	5.00
0.80	0.70	5.51	1.31	15.60	5.00
0.80	1.50	4.71	2.40	12.13	5.00
0.80	4.00	4.27	5.80	10.37	5.00
0.60	0.20	6.18	0.35	18.67	6.67
0.60	0.70	4.62	0.91	11.78	6.67
0.60	1.50	4.29	1.81	10.47	6.67
0.60	4.00	4.11	4.61	9.78	6.67
0.51	0.20	4.00	0.20	9.37	7.92
0.51	0.70	4.00	0.70	9.37	7.92
0.51	1.50	4.00	1.50	9.37	7.92
0.51	4.00	4.00	4.00	9.37	7.92
0.47	0.20	3.12	0.15	6.30	8.45
0.47	0.70	3.75	0.63	8.45	8.45
0.47	1.50	3.88	1.39	8.93	8.45
0.47	4.00	3.96	3.79	9.20	8.45

Table 6

Fig.14

Table 7

Internal ballistic parameters of motor before and after regulation with different nozzle throat radii

R_n/mm	$p ¯ f$ /MPa	$p ¯ o$ /MPa	$m ˙ ¯ f$ /（g·s^-1）	$m ˙ ¯ o$ /（g·s^-1）	$m ˙ ¯ f / m ˙ ¯ o$	I_sp/（m·s^-1）	F/N
5.12	20.00	3.64	136.59	78.26	1.75	2 011.53	432.18
4.57	16.78	4.55	121.36	90.07	1.35	2 067.98	437.23
3.96	12.76	6.40	102.25	114.25	0.89	2 154.83	466.52

Table 7

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序号	化学反应方程式	A_k /（cm³·mol^-1·s^-1）	β_k	E_ak /（cal·mol^-1）
1	CO+0.5O₂=CO₂	2.00×10⁹	0	12 000
2	H₂+0.5O₂=H₂O	2.85×10¹⁴	-1.0	40 000
3	CH₄+1.5O₂=CO+2H₂O	1.59×10¹²	0	47 800

结果来源	p_w/p₀
结果来源	x=0.344 3 m	x=0.492 2 m	x=0.573 3 m	x=0.672 4 m	x=0.852 4 m
Billig和Grenleski^［41］的实验结果	0.056 9	0.038 3	0.034 3	0.030 1	0.024 0
O’Brien等^［28］的数值结果	0.061 0	0.043 4	0.037 3	0.031 5	0.023 9
本文数值结果	0.057 9	0.041 3	0.035 0	0.029 3	0.021 7

方法	p_f /MPa	p_o/MPa	I_sp/（m·s^-1）	F/N
实验^［2］	4.38	4.17	2 069.76	111.25
数值模拟	4.42	4.38	2 230.41	121.82

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Numerical study on quasi⁃one⁃dimensional internal ballistics of throttling segregated fuel⁃oxidizer systems

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