Acoustic Fields generated by Solid Rockets in Ground Firing Test

Transcription

1 128 宇宙航空研究開発機構特別資料 JAXA-SP ,, (JAXA/ ), (JAXA/ ),,, (JAXA/), (JAXA/ ) Acoustic Fields generated by Solid Rockets in Ground Firing Test by Kota Fukuda, Seiji Tsutsumi, Kozo Fujii, Kyoichi Ui, Tatsuya Ishii, Hideshi Oinuma, Junichi Kazawa, and Kenji Minesugi (JAXA) ABSTRACT In JAXA, Computational Fluid Dynamics (CFD) is applied to examine acoustic field in rocket launching and the data is effectively used to design new launchers. Qualitative evaluation and comparison between calculation results and experimental data are necessary for further development of the CFD methodology. In this study, measurement of acoustic field is executed in two series of ground firing tests of solid rockets. Three types of microphones are used for the tests in order to attain those characteristics and applicability. The comparison shows that condenser microphone is the most applicable for a wide range of frequency. The obtained data are used for evaluation of an empirical method, NASA SP-72 and CFD methodology. From the results, it is cleared that the CFD methodology is effective for prediction of acoustics from solid rockets. ( ) NASA SP-72 [1] JAXA (JEDI) (CFD) [2]-[4] [4] CFD (Fig.8 ) JAXA 2 CFD NASA SP-72 NASA SP-72 CFD SP-72 2 CFD Kirchhoff CFD SP-72 CFD CFD JAXA SST NAL Fig.1 NAL-735 Table 1 Fig.2 1 Fig m 5 Table 2 2 ( )

2 第 40 回流体力学講演会 / 航空宇宙数値シミュレ ション技術シンポジウム 2008 論文集 129 Fig.1 NAL-735 motor Fig.2 Snapshot of first test 39m (63.5D e ) M5 50 M4 65 M3 M2 M1 h e = 3.2D e h = 2.4D e Far filed (1st and 2nd tests) 10m (16.3D e ) 10m (16.3D e ) M6 M7 3m (4.9D e ) 3m (4.9D e ) 3m (4.9D e ) M8 Near field (2nd test) Fig.3 Schematic layout of measured points and microphone setting position Table 1 Motor Spec. ICP h e = 3.2D e h = 0.0D e Table 2 Characteristics of microphones Fig.4 M1 (SPL) 3 SPL 2000Hz 2000Hz JAXA ICP 2000Hz 2000Hz Fig.5 M1 1 2 Hz Fig.6 1 SPL db db Fig Hz : M1, Condenser mic. 1st test : M1, Piezo mic. 1st test : M1, ICP mic. 1st test Fig.4 Comparison of SPLs measured with various microphones : M1, Condenser mic. 1st test : M1, Condenser mic. 2nd test Fig.5 Comparison of SPLs between first and second tests : M1, Condenser mic. 1st test : M2, Condenser mic. 1st test : M3, Condenser mic. 1st test : M4, Condenser mic. 1st test : M5, Condenser mic. 1st test Fig.6 Comparison of SPLs measured at each point

3 宇宙航空研究開発機構特別資料 JAXA-SP : M6, Piezo mic. 2nd test : M7, Piezo mic. 2nd test : M8, Piezo mic. 2nd test Fig.7 Comparison of SPLs measured at each point (near field) 3.1. NASA SP-72 SP-72 [1] 2 model 1 model 2 model 2 model 1 Fig.8 1% model 2 2 [2], [4] LES ( =1.174) JAXA NEC SX6 1 (8 CPUs) 250 Kirchhoff Fig.9 5D e 30D e 1/7 Pe / Pa= [Hz] Kirchhoff [6] -200[Hz] (Fig.2 ) Fig.10 Figs.11, 12 Kirchhoff 30D e 10D e Fig.8 Sketch of acoustic source location for NASA SP-72 (from NASA SP-72 [1] ) Kirchhoff surface 3.2. CFD CFD Fig.9 10 [2]-[4] JAXA Y X Fig.9 Cross section of computational grid on z=0 plane

4 第 40 回流体力学講演会 / 航空宇宙数値シミュレ ション技術シンポジウム 2008 論文集 131 Kirchhoff Z Y 3.2D e 3.2D e Kirchhoff Fig.10 Mirror image of kirchhoff surface Fig.11 Instantaneous flow patterns (Mach number) Fig.12 Instantaneous static pressure distribution P/Pe (db) (db) 2.36 (db) (db) Fig.13 SP-72 CFD SP-72 model 1 model 2 CFD SPL Kirchhoff CFD M1-3 SP-72 CFD SP-72 model 2 model 1 M4-5 CFD SPL SP-72 model 1, 2 CFD Kirchhoff M6-8 SP-72 CFD Kirchhoff 1.5 Mach Number 1.0 Fig.14 OA(Overall) CFD SP-72 CFD CFD [Hz] OA 1, 2 50 SP-72 M4, 5 CFD db SP-72 model 1 model 2 db CFD 55 Kirchhoff SP-72 M4, 5 M7 Fig.3 38 M4 SP-72 SP-72 SP-72 M4, 5 60-[Hz] 75[Hz] 60-[Hz] [7] M4, 5

5 132 宇宙航空研究開発機構特別資料 JAXA-SP : measured data (M1, 1st test) : measured data (M1, 2nd test) (mirror image) : measured data (M5, 1st test) : measured data (M5, 2nd test) (mirror image) (a) M1 point (e) M5 point : measured data (M2, 1st test) : measured data (M2, 2nd test) (mirror image) : measured data (M6, 2nd test) (mirror image) (b) M2 point (f) M6 point : measured data (M3, 1st test) : measured data (M3, 2nd test) : NASASP-72, model2 (mirror image) : measured data (M7, 2nd test) (mirror image) (c) M3 point (g) M7 point : measured data (M4, 1st test) : measured data (M4, 2nd test) (mirror image) : measured data (M8, 2nd test) (mirror image) (d) M4 point (h) M8 point Fig.13 Comparison of SPLs measured at each point

6 第 40 回流体力学講演会 / 航空宇宙数値シミュレ ション技術シンポジウム 2008 論文集 133 OA Angle from jet axis [deg] (a) Far field : 1st : 2nd (mirror image) : SP72, model1 : SP72, model2 JAXA L/D CFD NAL-735 SP-72 OA : 2nd (mirror image) : SP-72, model1 : SP-72, model Angle from jet axis [deg] (b) Near field Fig.14 Directional characteristics of OASPL (40-200[Hz]) JAXA NAL-735 NASA SP-72 CFD CFD NASA SP-72 CFD SP-72 db [1] Eldred, K. M., Acoustic Loads Generated by the Propulsion System, NASA SP-72, [2] Tsutsumi, S., Takaki, R., Shima, E., Fujii, K., Arita, M., Generation and Propagation of Pressure Waves from H-IIA Launch Vehicle at Lift-off, 46th AIAA Aerospace Seciences Meeting and Exhibit, , [3] Kawai, S., Tsutsumi, S., Takaki, R., Fujii, K., Computational Aeroacoustic Analysis of Overexpanded Supersonic Jet Impingement on a Flat Plate with/without Hole, 5th ASME/JSME Joint Fluids Engineering Conference, FEDSM , [4] Tsutsumi, S., Fukuda, K., Takaki, R., Shima, E., Fuji, K., Ui, K, Numerical Analysis of Acoustic Environment for Designing Launch-Pad of Advanced Solid Rocket, The 26th International Symposium on Space Technology and Science, 2008-g-05, [5],,,,,,,,, 40 /,, pp , [6] Yoerkie, C. A. and Larson, R. S., Prediction of Free-Field Noise Levels from Pole Microphone Measurements, AIAA 6th aeroacoustics conference, AIAA--1058, 19. [7] Temkin, S. and Dobbins, R. A., Attenuation and Dispersion of Sound by Particulate-Relaxation Process, J. of the Acoustical Society of America, Vol.40, No.2, pp , CFD SP-72