Computational Study on the Steady Loading Noise of Drone Propellers: Noise Source Modeling with the Lattice Boltzmann Method
Abstract In the present study, a new computational methodology is explored to compute the acoustic field of drone propellers using noise source modeling with the lattice Boltzmann method. A simple mathematical model of steady loading noise for predicting the blade passing frequency (BPF) tone and ha...
Ausführliche Beschreibung
Gespeichert in:
| Autor*in: |
Park, Chun Hyuk [verfasserIn] |
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| Format: |
E-Artikel |
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| Sprache: |
Englisch |
| Erschienen: |
2019 |
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| Schlagwörter: |
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| Anmerkung: |
© The Korean Society for Aeronautical & Space Sciences 2019 |
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| Übergeordnetes Werk: |
Enthalten in: International journal of aeronautical and space sciences - [Cham] : Springer International Publishing, 2009, 20(2019), 4 vom: 03. Juni, Seite 858-869 |
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| Übergeordnetes Werk: |
volume:20 ; year:2019 ; number:4 ; day:03 ; month:06 ; pages:858-869 |
| Links: |
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| DOI / URN: |
10.1007/s42405-019-00177-2 |
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| Katalog-ID: |
SPR038540983 |
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| 245 | 1 | 0 | |a Computational Study on the Steady Loading Noise of Drone Propellers: Noise Source Modeling with the Lattice Boltzmann Method |
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| 520 | |a Abstract In the present study, a new computational methodology is explored to compute the acoustic field of drone propellers using noise source modeling with the lattice Boltzmann method. A simple mathematical model of steady loading noise for predicting the blade passing frequency (BPF) tone and harmonics at low frequencies (100–1000 Hz) is proposed and tested for various types of drone propellers. The computed result is in a reasonably good agreement with NASA’s measured sound pressure level (SPL) for APC-SF and DJI-CF two-blade single drone propellers rotating at 3600–6000 revolutions per minute. It replicates well the feature of an even number of BPF harmonics for the tested model propellers, showing the decaying slope of %$-\,6%$ for the first two BPF and harmonic peaks in the SPL spectrum. Notably, the proposed steady loading noise model shows all components of RPS harmonics with different magnitudes for different blade sizes and rotor arrangements, such as tricopter and quadcopter. The proposed method can be used for predicting and analyzing tones at low frequencies for various types of open rotor systems, such as multicopters and distributed electric propulsion vehicles. | ||
| 650 | 4 | |a Drone propeller noise |7 (dpeaa)DE-He213 | |
| 650 | 4 | |a Computational aeroacoustics |7 (dpeaa)DE-He213 | |
| 650 | 4 | |a Steady loading noise source modeling |7 (dpeaa)DE-He213 | |
| 650 | 4 | |a Lattice Boltzmann method |7 (dpeaa)DE-He213 | |
| 700 | 1 | |a Kim, Dae Han |4 aut | |
| 700 | 1 | |a Moon, Young J. |0 (orcid)0000-0002-0555-0744 |4 aut | |
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10.1007/s42405-019-00177-2 doi (DE-627)SPR038540983 (SPR)s42405-019-00177-2-e DE-627 ger DE-627 rakwb eng Park, Chun Hyuk verfasserin aut Computational Study on the Steady Loading Noise of Drone Propellers: Noise Source Modeling with the Lattice Boltzmann Method 2019 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © The Korean Society for Aeronautical & Space Sciences 2019 Abstract In the present study, a new computational methodology is explored to compute the acoustic field of drone propellers using noise source modeling with the lattice Boltzmann method. A simple mathematical model of steady loading noise for predicting the blade passing frequency (BPF) tone and harmonics at low frequencies (100–1000 Hz) is proposed and tested for various types of drone propellers. The computed result is in a reasonably good agreement with NASA’s measured sound pressure level (SPL) for APC-SF and DJI-CF two-blade single drone propellers rotating at 3600–6000 revolutions per minute. It replicates well the feature of an even number of BPF harmonics for the tested model propellers, showing the decaying slope of %$-\,6%$ for the first two BPF and harmonic peaks in the SPL spectrum. Notably, the proposed steady loading noise model shows all components of RPS harmonics with different magnitudes for different blade sizes and rotor arrangements, such as tricopter and quadcopter. The proposed method can be used for predicting and analyzing tones at low frequencies for various types of open rotor systems, such as multicopters and distributed electric propulsion vehicles. Drone propeller noise (dpeaa)DE-He213 Computational aeroacoustics (dpeaa)DE-He213 Steady loading noise source modeling (dpeaa)DE-He213 Lattice Boltzmann method (dpeaa)DE-He213 Kim, Dae Han aut Moon, Young J. (orcid)0000-0002-0555-0744 aut Enthalten in International journal of aeronautical and space sciences [Cham] : Springer International Publishing, 2009 20(2019), 4 vom: 03. Juni, Seite 858-869 (DE-627)1015522505 (DE-600)2922594-2 2093-2480 nnns volume:20 year:2019 number:4 day:03 month:06 pages:858-869 https://dx.doi.org/10.1007/s42405-019-00177-2 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_266 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 20 2019 4 03 06 858-869 |
| spelling |
10.1007/s42405-019-00177-2 doi (DE-627)SPR038540983 (SPR)s42405-019-00177-2-e DE-627 ger DE-627 rakwb eng Park, Chun Hyuk verfasserin aut Computational Study on the Steady Loading Noise of Drone Propellers: Noise Source Modeling with the Lattice Boltzmann Method 2019 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © The Korean Society for Aeronautical & Space Sciences 2019 Abstract In the present study, a new computational methodology is explored to compute the acoustic field of drone propellers using noise source modeling with the lattice Boltzmann method. A simple mathematical model of steady loading noise for predicting the blade passing frequency (BPF) tone and harmonics at low frequencies (100–1000 Hz) is proposed and tested for various types of drone propellers. The computed result is in a reasonably good agreement with NASA’s measured sound pressure level (SPL) for APC-SF and DJI-CF two-blade single drone propellers rotating at 3600–6000 revolutions per minute. It replicates well the feature of an even number of BPF harmonics for the tested model propellers, showing the decaying slope of %$-\,6%$ for the first two BPF and harmonic peaks in the SPL spectrum. Notably, the proposed steady loading noise model shows all components of RPS harmonics with different magnitudes for different blade sizes and rotor arrangements, such as tricopter and quadcopter. The proposed method can be used for predicting and analyzing tones at low frequencies for various types of open rotor systems, such as multicopters and distributed electric propulsion vehicles. Drone propeller noise (dpeaa)DE-He213 Computational aeroacoustics (dpeaa)DE-He213 Steady loading noise source modeling (dpeaa)DE-He213 Lattice Boltzmann method (dpeaa)DE-He213 Kim, Dae Han aut Moon, Young J. (orcid)0000-0002-0555-0744 aut Enthalten in International journal of aeronautical and space sciences [Cham] : Springer International Publishing, 2009 20(2019), 4 vom: 03. Juni, Seite 858-869 (DE-627)1015522505 (DE-600)2922594-2 2093-2480 nnns volume:20 year:2019 number:4 day:03 month:06 pages:858-869 https://dx.doi.org/10.1007/s42405-019-00177-2 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_266 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 20 2019 4 03 06 858-869 |
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10.1007/s42405-019-00177-2 doi (DE-627)SPR038540983 (SPR)s42405-019-00177-2-e DE-627 ger DE-627 rakwb eng Park, Chun Hyuk verfasserin aut Computational Study on the Steady Loading Noise of Drone Propellers: Noise Source Modeling with the Lattice Boltzmann Method 2019 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © The Korean Society for Aeronautical & Space Sciences 2019 Abstract In the present study, a new computational methodology is explored to compute the acoustic field of drone propellers using noise source modeling with the lattice Boltzmann method. A simple mathematical model of steady loading noise for predicting the blade passing frequency (BPF) tone and harmonics at low frequencies (100–1000 Hz) is proposed and tested for various types of drone propellers. The computed result is in a reasonably good agreement with NASA’s measured sound pressure level (SPL) for APC-SF and DJI-CF two-blade single drone propellers rotating at 3600–6000 revolutions per minute. It replicates well the feature of an even number of BPF harmonics for the tested model propellers, showing the decaying slope of %$-\,6%$ for the first two BPF and harmonic peaks in the SPL spectrum. Notably, the proposed steady loading noise model shows all components of RPS harmonics with different magnitudes for different blade sizes and rotor arrangements, such as tricopter and quadcopter. The proposed method can be used for predicting and analyzing tones at low frequencies for various types of open rotor systems, such as multicopters and distributed electric propulsion vehicles. Drone propeller noise (dpeaa)DE-He213 Computational aeroacoustics (dpeaa)DE-He213 Steady loading noise source modeling (dpeaa)DE-He213 Lattice Boltzmann method (dpeaa)DE-He213 Kim, Dae Han aut Moon, Young J. (orcid)0000-0002-0555-0744 aut Enthalten in International journal of aeronautical and space sciences [Cham] : Springer International Publishing, 2009 20(2019), 4 vom: 03. Juni, Seite 858-869 (DE-627)1015522505 (DE-600)2922594-2 2093-2480 nnns volume:20 year:2019 number:4 day:03 month:06 pages:858-869 https://dx.doi.org/10.1007/s42405-019-00177-2 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_266 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 20 2019 4 03 06 858-869 |
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10.1007/s42405-019-00177-2 doi (DE-627)SPR038540983 (SPR)s42405-019-00177-2-e DE-627 ger DE-627 rakwb eng Park, Chun Hyuk verfasserin aut Computational Study on the Steady Loading Noise of Drone Propellers: Noise Source Modeling with the Lattice Boltzmann Method 2019 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © The Korean Society for Aeronautical & Space Sciences 2019 Abstract In the present study, a new computational methodology is explored to compute the acoustic field of drone propellers using noise source modeling with the lattice Boltzmann method. A simple mathematical model of steady loading noise for predicting the blade passing frequency (BPF) tone and harmonics at low frequencies (100–1000 Hz) is proposed and tested for various types of drone propellers. The computed result is in a reasonably good agreement with NASA’s measured sound pressure level (SPL) for APC-SF and DJI-CF two-blade single drone propellers rotating at 3600–6000 revolutions per minute. It replicates well the feature of an even number of BPF harmonics for the tested model propellers, showing the decaying slope of %$-\,6%$ for the first two BPF and harmonic peaks in the SPL spectrum. Notably, the proposed steady loading noise model shows all components of RPS harmonics with different magnitudes for different blade sizes and rotor arrangements, such as tricopter and quadcopter. The proposed method can be used for predicting and analyzing tones at low frequencies for various types of open rotor systems, such as multicopters and distributed electric propulsion vehicles. Drone propeller noise (dpeaa)DE-He213 Computational aeroacoustics (dpeaa)DE-He213 Steady loading noise source modeling (dpeaa)DE-He213 Lattice Boltzmann method (dpeaa)DE-He213 Kim, Dae Han aut Moon, Young J. (orcid)0000-0002-0555-0744 aut Enthalten in International journal of aeronautical and space sciences [Cham] : Springer International Publishing, 2009 20(2019), 4 vom: 03. Juni, Seite 858-869 (DE-627)1015522505 (DE-600)2922594-2 2093-2480 nnns volume:20 year:2019 number:4 day:03 month:06 pages:858-869 https://dx.doi.org/10.1007/s42405-019-00177-2 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_266 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 20 2019 4 03 06 858-869 |
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10.1007/s42405-019-00177-2 doi (DE-627)SPR038540983 (SPR)s42405-019-00177-2-e DE-627 ger DE-627 rakwb eng Park, Chun Hyuk verfasserin aut Computational Study on the Steady Loading Noise of Drone Propellers: Noise Source Modeling with the Lattice Boltzmann Method 2019 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © The Korean Society for Aeronautical & Space Sciences 2019 Abstract In the present study, a new computational methodology is explored to compute the acoustic field of drone propellers using noise source modeling with the lattice Boltzmann method. A simple mathematical model of steady loading noise for predicting the blade passing frequency (BPF) tone and harmonics at low frequencies (100–1000 Hz) is proposed and tested for various types of drone propellers. The computed result is in a reasonably good agreement with NASA’s measured sound pressure level (SPL) for APC-SF and DJI-CF two-blade single drone propellers rotating at 3600–6000 revolutions per minute. It replicates well the feature of an even number of BPF harmonics for the tested model propellers, showing the decaying slope of %$-\,6%$ for the first two BPF and harmonic peaks in the SPL spectrum. Notably, the proposed steady loading noise model shows all components of RPS harmonics with different magnitudes for different blade sizes and rotor arrangements, such as tricopter and quadcopter. The proposed method can be used for predicting and analyzing tones at low frequencies for various types of open rotor systems, such as multicopters and distributed electric propulsion vehicles. Drone propeller noise (dpeaa)DE-He213 Computational aeroacoustics (dpeaa)DE-He213 Steady loading noise source modeling (dpeaa)DE-He213 Lattice Boltzmann method (dpeaa)DE-He213 Kim, Dae Han aut Moon, Young J. (orcid)0000-0002-0555-0744 aut Enthalten in International journal of aeronautical and space sciences [Cham] : Springer International Publishing, 2009 20(2019), 4 vom: 03. Juni, Seite 858-869 (DE-627)1015522505 (DE-600)2922594-2 2093-2480 nnns volume:20 year:2019 number:4 day:03 month:06 pages:858-869 https://dx.doi.org/10.1007/s42405-019-00177-2 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_266 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 20 2019 4 03 06 858-869 |
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Park, Chun Hyuk @@aut@@ Kim, Dae Han @@aut@@ Moon, Young J. @@aut@@ |
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Park, Chun Hyuk |
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Park, Chun Hyuk misc Drone propeller noise misc Computational aeroacoustics misc Steady loading noise source modeling misc Lattice Boltzmann method Computational Study on the Steady Loading Noise of Drone Propellers: Noise Source Modeling with the Lattice Boltzmann Method |
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Computational Study on the Steady Loading Noise of Drone Propellers: Noise Source Modeling with the Lattice Boltzmann Method Drone propeller noise (dpeaa)DE-He213 Computational aeroacoustics (dpeaa)DE-He213 Steady loading noise source modeling (dpeaa)DE-He213 Lattice Boltzmann method (dpeaa)DE-He213 |
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Computational Study on the Steady Loading Noise of Drone Propellers: Noise Source Modeling with the Lattice Boltzmann Method |
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Computational Study on the Steady Loading Noise of Drone Propellers: Noise Source Modeling with the Lattice Boltzmann Method |
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computational study on the steady loading noise of drone propellers: noise source modeling with the lattice boltzmann method |
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Computational Study on the Steady Loading Noise of Drone Propellers: Noise Source Modeling with the Lattice Boltzmann Method |
| abstract |
Abstract In the present study, a new computational methodology is explored to compute the acoustic field of drone propellers using noise source modeling with the lattice Boltzmann method. A simple mathematical model of steady loading noise for predicting the blade passing frequency (BPF) tone and harmonics at low frequencies (100–1000 Hz) is proposed and tested for various types of drone propellers. The computed result is in a reasonably good agreement with NASA’s measured sound pressure level (SPL) for APC-SF and DJI-CF two-blade single drone propellers rotating at 3600–6000 revolutions per minute. It replicates well the feature of an even number of BPF harmonics for the tested model propellers, showing the decaying slope of %$-\,6%$ for the first two BPF and harmonic peaks in the SPL spectrum. Notably, the proposed steady loading noise model shows all components of RPS harmonics with different magnitudes for different blade sizes and rotor arrangements, such as tricopter and quadcopter. The proposed method can be used for predicting and analyzing tones at low frequencies for various types of open rotor systems, such as multicopters and distributed electric propulsion vehicles. © The Korean Society for Aeronautical & Space Sciences 2019 |
| abstractGer |
Abstract In the present study, a new computational methodology is explored to compute the acoustic field of drone propellers using noise source modeling with the lattice Boltzmann method. A simple mathematical model of steady loading noise for predicting the blade passing frequency (BPF) tone and harmonics at low frequencies (100–1000 Hz) is proposed and tested for various types of drone propellers. The computed result is in a reasonably good agreement with NASA’s measured sound pressure level (SPL) for APC-SF and DJI-CF two-blade single drone propellers rotating at 3600–6000 revolutions per minute. It replicates well the feature of an even number of BPF harmonics for the tested model propellers, showing the decaying slope of %$-\,6%$ for the first two BPF and harmonic peaks in the SPL spectrum. Notably, the proposed steady loading noise model shows all components of RPS harmonics with different magnitudes for different blade sizes and rotor arrangements, such as tricopter and quadcopter. The proposed method can be used for predicting and analyzing tones at low frequencies for various types of open rotor systems, such as multicopters and distributed electric propulsion vehicles. © The Korean Society for Aeronautical & Space Sciences 2019 |
| abstract_unstemmed |
Abstract In the present study, a new computational methodology is explored to compute the acoustic field of drone propellers using noise source modeling with the lattice Boltzmann method. A simple mathematical model of steady loading noise for predicting the blade passing frequency (BPF) tone and harmonics at low frequencies (100–1000 Hz) is proposed and tested for various types of drone propellers. The computed result is in a reasonably good agreement with NASA’s measured sound pressure level (SPL) for APC-SF and DJI-CF two-blade single drone propellers rotating at 3600–6000 revolutions per minute. It replicates well the feature of an even number of BPF harmonics for the tested model propellers, showing the decaying slope of %$-\,6%$ for the first two BPF and harmonic peaks in the SPL spectrum. Notably, the proposed steady loading noise model shows all components of RPS harmonics with different magnitudes for different blade sizes and rotor arrangements, such as tricopter and quadcopter. The proposed method can be used for predicting and analyzing tones at low frequencies for various types of open rotor systems, such as multicopters and distributed electric propulsion vehicles. © The Korean Society for Aeronautical & Space Sciences 2019 |
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Computational Study on the Steady Loading Noise of Drone Propellers: Noise Source Modeling with the Lattice Boltzmann Method |
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Kim, Dae Han Moon, Young J. |
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