液体火箭发动机喷焰多波段辐射信号高度律
收稿日期: 2024-04-22
修回日期: 2024-05-25
录用日期: 2024-06-25
网络出版日期: 2024-07-08
基金资助
国家自然科学基金(U22B2045)
Altitude-scaling law for multi-band radiation signals from liquid-propellant rocket engine exhaust plumes
Received date: 2024-04-22
Revised date: 2024-05-25
Accepted date: 2024-06-25
Online published: 2024-07-08
Supported by
National Natural Science Foundation of China(U22B2045)
实际探测中火箭发动机喷焰单波段红外辐射强度与飞行高度之间往往是一种非单调关系，在反演高度时，会出现多值性问题。以典型液体火箭发动机尾喷焰为研究对象，基于计算流体力学（CFD）方法计算尾喷焰反应流场的温度、压力和组分信息，采用视在光线（LOS）法并结合NASA-SP-3080高温气体辐射物性数据库计算尾喷焰本征红外辐射信号，采用Modtran软件获取11~61 km俯视和水平观测时的大气透过率，进而计算得到火箭发动机尾喷焰表观辐射信号。从液体火箭发动机推进剂元素构成和气体辐射产生机理出发，提出基于多波段表观辐射强度构造无量纲特征参数，即所谓的相对二阶差（RSOD），作为尾喷焰红外辐射高度律的表征参数，分析获得了RSOD和飞行高度之间映射关系。研究发现，首先通过多波段辐射强度二次构造的辐射特征量，能够获得其与飞行高度的单调关联关系，且经过不同推力验证，具有一定普适性。然后，利用这种单调关系，能较好地反演发动机所在高度，在31~61 km范围内，反演结果更为准确。最后发现不同推进剂类型的RSOD区分度较好，推测利用RSOD信息作为特征量有利于区分不同的发动机类型。
关键词： 液体火箭喷焰; 表观红外辐射; 多波段; 相对二阶差（RSOD）; 高度律
孙一强 , 朱檀枭 , 牛青林 , 贺志宏 , 董士奎 . 液体火箭发动机喷焰多波段辐射信号高度律[J]. 航空学报, 2024 , 45(24) : 630568 -630568 . DOI: 10.7527/S1000-6893.2024.30568
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.
| 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. |
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