液体火箭发动机喷焰多波段辐射信号高度律

doi:10.7527/S1000-6893.2024.30568

Abstract

Abstract:

The relationship between the intensity of single-band infrared radiation from rocket motor plumes and flight altitude is often non-monotonic in actual detections. The issue of multivalence occurs in height inversion. This paper focuses on analyzing many typical liquid propellant rocket engine plumes. Computational Fluid Dynamics（CFD）is used to determine the temperature， pressure， and component information of the reactive flow field of the plume. The Light-on-Sight（LOS）method and the NASA-SP-3080 high-temperature gas radiative property database are employed to calculate the intrinsic infrared radiation signals of the plume. Additionally， the Modtran program is used to determine the atmospheric transmittance at altitudes ranging from 11 to 61 km in both top-down and horizontal observations. Subsequently， the apparent radiation signals of the rocket engine plume are computed. On the basis of the element composition of the liquid propellant and the mechanism of gas radiation generation， it is proposed to construct a dimensionless characteristic parameter based on the multi-band apparent radiance， the so-called Relative Second Order Difference（RSOD）， as the characterization parameter of the altitude-scaling law of the plume infrared radiation. The monotonous mapping relationship between the RSOD and the flight altitude is obtained analytically. It is found that the monotonic correlation between the radiative signatures constructed through the quadratic construction of multi-band radiated signals and the flight altitude can be obtained， and it is verified by different thrusts that the relationship is universal to a certain extent. Then， using this monotonic relation， better inversion altitude results can be obtained， and the inversion accuracy is higher in the range of 31-61 km. Finally， it is found that the RSOD differentiation is better for different engine propellant types， and it is speculated that the use of RSOD information as a characteristic quantity can be beneficial to differentiating engine types.

Key words: liquid-propellant rocket engine exhaust plume, apparent infrared radiation, multi-band, Relative Second Order Difference (RSOD), altitude-scaling law

CLC Number:

Yiqiang SUN, Tanxiao ZHU, Qinglin NIU, Zhihong HE, Shikui DONG. Altitude-scaling law for multi-band radiation signals from liquid-propellant rocket engine exhaust plumes[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(24): 630568.

Figures/Tables 31

Fig.1

Fig.2

Fig.3

Table 1

Performance parameters of RD-180 rocket engine［21，30-32］

参数	指标
推进剂	LOX/RP-1
真空推力 $F$ /kN	4 152
燃烧室压力 $P c$ /bar	257
氧燃比 $O / F$	2.72
膨胀比 $A e / A t$	37
喷口出口直径 $D e$ /m	1.43
运载火箭	Atlas III/Atlas V
发动机数目	1（2喷管）

Table 1

Table 2

Equivalent nozzle exit parameters for RD-180 engine

等效喷口出口参数		数值
出口半径 $R e$ /m		1.049
出口压力 $P e$ /Pa		70 065
出口温度 $T e$ /K		1 935
出口速度 $U e$ /（m·s^-1）		3 340
出口气体质量分数	H	0.000 013
	O	0
	OH	0.000 119
	H₂O	0.284 044
	CO	0.239 839
	CO₂	0.470 111
	H₂	0.005 871
	O₂	0.000 003
	N₂	0

Table 2

Fig.4

Table 3

Table 4

Grid distributions of different computational domains

飞行高度 h/km	计算域		网格数
飞行高度 h/km	$L f$ /m	$R f$ /m	g	d
11	500	50	1 000	80
15~25	1 500	80	1 500	100
31~61	2 500	120	2 000	150

Table 4

Fig.5

Fig.6

Fig.7

Fig.8

Table 5

Table 6

Fig.9

Fig.10

Fig.11

Table 7

Performance parameters of RS-56 and RD-191 rocket motors

发动机名称	RS-56-OBA	RS-56-OSA	RD-191
推进剂	LOX/RP-1
真空推力 $F$ /kN	1 047	380.6	2 090
燃烧室压力 $P c$ /bar	44.68	51.37	257
氧燃比 $O / F$	2.25	2.27	2.6
膨胀比 $A e / A t$	8	25	37
喷口出口直径 $D e$ /m	1.32	1.32	1.43
运载火箭	Atlas II		Angara
发动机数目	2	1	1

Table 7

Fig.12

Fig.13

Table 8

Performance parameters of RD-275M and RS-68 rocket motors

发动机名称	RD-275M	RS-68
推进剂	UDMH/N₂O₄	LOX/LH₂
真空推力 $F$ /kN	1 830	3 313
燃烧室压力 $P c$ /bar	165	97.2
氧燃比 $O / F$	2.67	6.0
膨胀比 $A e / A t$	26.2	21.5
喷口出口直径 $D e$ /m	1.431	2.44
运载火箭	Proton-M	Delta IV
发动机数目	3	1

Table 8

Table 9

Nozzle exit parameters for RD-275M and RS-68 engines

发动机名称		RD-275M	RS-68
出口压力 $P e$ /Pa		62 903.7	47 594.7
出口温度 $T e$ /K		1 610.2	1 673.0
出口速度 $U e$ /（m·s^-1）		3 089.3	4 052.9
出口气体质量分数	H	0.000 001	0.000 006
	O	0	0
	OH	0.000 004	0.000 017
	H₂O	0.289 270	0.965 127
	CO	0.071 850	0
	CO₂	0.286 180	0
	H₂	0.004 190	0.034 850
	O₂	0	0
	N₂	0.348 505	0

Table 9

Fig.14

Fig.15

Fig.16

Fig.17

Fig.18

Table 10

Coefficients and R2 for RSODh

发动机	探测方式	$r 0$	$r 1$	$h 0$	$R 2$
RD-180	水平	-1.340	1.187	31.878	0.985
RD-180	俯视	-0.970	0.987	35.902	0.963
RD-191	水平	-2.066	1.798	36.295	0.992
RD-191	俯视	-1.729	1.566	41.417	0.961
RS-56	水平	-1.484	1.317	32.842	0.989
RS-56	俯视	-1.067	1.071	37.006	0.967

Table 10

Fig.19

Fig.20

Fig.21

References 41

1	SIMMONS F. Rocket exhaust plume phenomenology［M］. Reston： AIAA， 2000.
2	HIGGINS C J， SMITHSON T， COXHILL I， et al. Characterising the infrared signature of a liquid propellant engine plume［C］∥Proceedings of the 52nd AIAA/SAE/ASEE Joint Propulsion Conference. Reston： AIAA， 2016.
3	STOWE R， RINGUETTE S， FOURNIER P， et al. Effect of flight and motor operating conditions on infrared signature predictions of rocket exhaust plumes［J］. International Journal of Energetic Materials and Chemical Propulsion， 2015， 14（1）： 29-56.
4	CALHOON W JR， KENZAKOWSKI D. Flowfield and radiation analysis of missile exhaust plumes using a turbulent-chemistry interaction model［C］∥Proceedings of the 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston： AIAA， 2000.
5	PAIVA C， SLUSHER H. Space-based missile exhaust plume sensing： Strategies for DTCI of liquid and solid IRBM systems［C］∥Proceedings of the Space 2005. Reston： AIAA， 2005.
6	NIU Q L， FU D B， DONG S K， et al. A simplified model for fast estimating infrared thermal radiation of low-altitude under-expanded exhaust plumes［J］. International Journal of Heat and Mass Transfer， 2019， 136： 276-287.
7	SMOOT L， SIMONSEN J， WILLIAMS G. Exhaust plume prediction model for a low-altitude supersonic missile［C］∥Proceedings of the 8th Joint Propulsion Specialist Conference. Reston： AIAA， 1972.
8	VITKIN E I， KARELIN V G， KIRILLOV A A， et al. A physico-mathematical model of rocket exhaust plumes［J］. International Journal of Heat and Mass Transfer， 1997， 40（5）： 1227-1241.
9	LI J L， BAI L， BAI J Y， et al. Narrow-band infrared radiation characteristics of rocket exhaust plume by using correction function related to thermodynamic state［J］. Infrared Physics and Technology， 2022， 125： 104260.
10	ZIRKIND R. Radiation from rocket-exhaust plumes［J］. Symposium （International） on Combustion， 1967， 11（1）： 613-620.
11	LIU Z Y， YE Q， DING F， et al. Study on the influence of flight altitude on the rocket plume radiation enhancement effect caused by afterburning［J］. International Journal of Aeronautical and Space Sciences， 2021， 22（5）： 1019-1030.
12	KIM S， KIM S， KIM M， et al. Infrared signature of NEPE， HTPB rocket plume under varying flight conditions and motor size［J］. Infrared Physics and Technology， 2021， 112： 103590.
13	DASH S M， PEARCE B E， PERGAMENT H S， et al. Prediction of rocket plume flowfields for infrared signature studies［J］. Journal of Spacecraft and Rockets， 1980， 17（3）： 190-199.
14	WOODROFFE J. One-dimensional model for low-altitude rocket exhaust plumes［C］∥Proceedings of the 13th Aerospace Sciences Meeting. Reston： AIAA， 1975.
15	NIE W S， FENG S J， XIE Q F， et al. Numerical simulation of liquid rocket exhaust plume radiation［C］∥Proceedings of the 39th AIAA Thermophysics Conference. Reston： AIAA， 2007.
16	ZHOU Z T， WANG X， LU C Y， et al. Numerical analysis on thermal environment of liquid rocket with afterburning under different altitudes［J］. Applied Thermal Engineering， 2020， 178： 115584.
17	NIU Q L， DUAN X H， MENG X Y， et al. Numerical analysis of point-source infrared radiation phenomena of rocket exhaust plumes at low and middle altitudes［J］. Infrared Physics & Technology， 2019， 99： 28-38.
18	SUN Y Q， DONG S K， NIU Q L， et al. NIPC-based uncertainty analysis of infrared radiation from rocket exhaust plumes caused by nozzle exit conditions［J］. Infrared Physics & Technology， 2020， 108： 103376.
19	NIU Q L， HE Z H， DONG S K. IR radiation characteristics of rocket exhaust plumes under varying motor operating conditions［J］. Chinese Journal of Aeronautics， 2017， 30（3）： 1101-1114.
20	GORDON S， MCBRIDE B J. Computer program for calculation of complex chemical equilibrium compositions and applications. Part 1： Analysis［M］. Ohio： NASA Lewis Research Center， 1994： 2-3.
21	SUTTON G P， BIBLARZ O. Rocket propulsion elements［M］. 8th. ed. New Jersey： John Wiley & Sons， Inc， 2010， 18-51.
22	牛青林. 连续流域高速目标辐射现象学研究［D］. 哈尔滨：哈尔滨工业大学， 2019： 27-28.
	NIU Q L. Phenomenological study on radiation of high-speed targets in continuous basins［D］.Harbin： Harbin Institute of Technology， 2019： 27-28 （in Chinese）.
23	WANG W， WEI Z， ZHANG Q， et al. Study on infrared signature of solid rocket motor afterburning exhaust plume［C］∥46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston： AIAA， 2010.
24	KRAKOW B， BABROV H J， MACLAY G J， et al. Use of the Curtis-Godson approximation in calculations of radiant heating by inhomogeneous hot gases［J］. Applied Optics， 1966， 5（11）： 1791-1800.
25	LUDWIG C B， MALKMUS W， REARDON J， et al. Handbook of infrared radiation from combustion gases［M］. Washington， D.C.： NASA Marshall Space Flight Center， 1973： 220-223.
26	余其铮. 辐射换热原理［M］. 哈尔滨：哈尔滨工业大学出版社， 2000： 10-12.
	YU Q Z. Radiation heat transfer principle［M］. Harbin： Harbin Institute of Technology Press， 2000： 10-12 （in Chinese）.
27	BERK G A， ACHARYA P， CHETWYND J， et al. ADLER-GOLDEN. Modtran4 user’s manual［M］. Ohio： Air Force Research Laboratory， 1999.
28	AVITAL G， COHEN Y， GAMSS L， et al. Experimental and computational study of infrared emission from underexpanded rocket exhaust plumes［J］. Journal of Thermophysics and Heat Transfer， 2001， 15（4）： 377-383.
29	OZAWA T， GARRISON M B， LEVIN D A. Accurate molecular and soot infrared radiation model for high-temperature flows［J］. Journal of Thermophysics and Heat Transfer， 2007， 21（1）： 19-27.
30	POPP M， TANNER L， KATORGIN B， et al. RD-180 engine production and flight experience［C］∥Proceedings of the 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston： AIAA， 2004.
31	HAGGER R， JOYNER C， CHELKIS F. Kerosene booster engine-use for atlas commercial orbital transportation service capabilities and more［C］∥Proceedings of the 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston： AIAA， 2006.
32	KATORGIN B， CHVANOV V， YU F， et al. Atlas with RD-180 now［C］∥Proceedings of the 37th Joint Propulsion Conference and Exhibit. Reston： AIAA， 2001.
33	PLASTININ Y， KARABADZHAK G， KHMELININ B， et al. Investigation of soot density in the LOX/kerosene engine booster exhaust of Atlas II and Atlas III from remote measurements of radiation intensity［C］∥Proceedings of the 43rd AIAA Aerospace Sciences Meeting and Exhibit. Reston： AIAA， 2005.
34	BARTON P， PEARCE B， FREEMAN G， et al. Spectral imagery data and mechanisms［C］∥Proceedings of the 39th Aerospace Sciences Meeting and Exhibit. Reston： AIAA， 2001.
35	KATORGIN B， CHVANOV V， CHELKIS F， et al. RD-180 program history［C］∥Proceedings of the 37th Joint Propulsion Conference and Exhibit. Reston： AIAA， 2001.
36	RAO R， SINHA K， CANDLER G， et al. Numerical simulations of Atlas II rocket motor plumes［C］∥Proceedings of the 35th Joint Propulsion Conference and Exhibit. Reston： AIAA， 1999.
37	VISWANATH K， BRENTNER K S， GIMELSHEIN S F， et al. Investigation of soot combustion in underexpanded jet plume flows［J］. Journal of Thermophysics and Heat Transfer， 2005， 19（3）： 282-293.
38	PLASTININ Y， KARABDZHAK G， KHMELININ B， et al. Ultraviolet， visible and infrared spectra modeling for solid and liquid-fuel rocket exhausts［C］∥Proceedings of the 39th Aerospace Sciences Meeting and Exhibit. Reston： AIAA， 2001.
39	JONES J P， KUFFEL L， SORTO-RAMOS E， et al. Investigating the legacy of air-breathing and rocket propulsion systems［C］∥Proceedings of the AIAA Propulsion and Energy 2020 Forum. Reston： AIAA， 2020.
40	SOLLER S， WAGNER R， KIRCHBERGER C， et al. characterisation of combustion and heat transfer using GOX/Kerosene in a single-element rocket combustor［C］‍∥Proceedings of the 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston： AIAA， 2005.
41	ALLGOOD D， AHUJA V. Computational plume modeling of conceptual ARES vehicle stage tests［C］∥Proceedings of the 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston： AIAA， 2007.

飞行时间t/s	飞行高度h/km	飞行速度V/（m·s^-1）	大气压力P_∞/Pa	大气温度T_∞/K
62.69	11	414.26	22 632	216.65
73.69	15	550.19	12 044	216.65
87.46	21	793.32	4 677.8	217.65
96.22	25	961.23	2 511.0	221.65
107.17	31	1 226.74	1 008.20	227.65
114.81	35	1 417.76	558.92	237.05
124.14	41	1 703.44	242.39	253.85
130.31	45	1 900.92	143.13	265.05
139.52	51	2 221.28	66.94	270.65
145.11	55	2 441.25	39.97	259.45
153.27	61	2 791.95	17.66	242.65

h/ km	表观辐射强度/（W·sr^-1）
h/ km	2.7~3.0 μm	4.2~4.5 μm	3.7~4.8 μm	7.7~9.5 μm
11	650 164.3	24 296.6	451 535.6	288 750.4
15	1 806 391.0	89 115.7	1 177 685.7	561 602.2
21	3 734 857.6	414 252.8	2 473 676.6	686 605.7
25	4 409 546.4	962 849.5	3 588 292.1	574 781.6
31	3 730 992.5	2 246 681.3	4 817 205.5	374 466.5
35	2 872 447.4	2 914 147.5	5 063 578.5	260 125.3
41	1 868 262.1	3 242 472.9	4 476 037.9	173 789.3
45	1 405 029.8	3 025 619.3	3 826 237.2	143 084.6
51	697 687.6	1 966 429.4	2 309 414.6	93 278.2
55	358 444.7	1 210 248.2	1 391 954.7	64 849.1
61	178 226.5	653 674.4	755 557.3	44 783.3

h/ km	表观辐射强度/（W·sr^-1）
h/ km	2.7~3.0 μm	4.2~4.5 μm	3.7~4.8 μm	7.7~9.5 μm
11	1 004 666.6	1 560.5	616 546.3	452 390.0
15	3 966 876.9	56 815.5	2 511 613.0	1 078 757.8
21	7 536 788.5	1 095 478.0	7 711 916.9	1 498 686.3
25	8 784 653.3	3 116 166.6	11 699 000.0	1 372 791.5
31	7 652 861.2	7 220 551.5	14 273 600.0	1 002 264.6
35	6 103 040.4	9 216 720.9	14 254 200.0	746 998.4
41	4 080 041.5	10 353 600.0	12 612 500.0	530 745.4
45	3 027 854.3	9 754 882.7	11 162 000.0	442 896.8
51	1 466 582.5	6 204 441.3	6 878 999.0	283 259.7
55	714 409.9	3 530 278.1	3 931 006.1	182 360.3
61	319 869.9	1 856 914.8	2 108 277.1	105 357.1

Altitude-scaling law for multi-band radiation signals from liquid-propellant rocket engine exhaust plumes

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

Figures/Tables 31

References 41

Related Articles 1

Recommended Articles

Metrics

Comments