Optimal design for low sonic boom based on CoKriging surrogate model
Accurately predicting and effectively reducing sonic boom levels is one of the key issues in the development of the new generation of green supersonic civil aircraft. In order to improve the efficiency of low sonic boom optimal design for supersonic civil aircraft, a multi-fidelity optimal design pr...
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| Format: | Article |
| Language: | zho |
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Editorial Department of Advances in Aeronautical Science and Engineering
2025-06-01
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| Series: | Hangkong gongcheng jinzhan |
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| Online Access: | http://hkgcjz.cnjournals.com/hkgcjz/article/abstract/2023278 |
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| author | ZHANG Hanqi XU Yue ZHONG Min LI Yan |
| author_facet | ZHANG Hanqi XU Yue ZHONG Min LI Yan |
| author_sort | ZHANG Hanqi |
| collection | DOAJ |
| description | Accurately predicting and effectively reducing sonic boom levels is one of the key issues in the development of the new generation of green supersonic civil aircraft. In order to improve the efficiency of low sonic boom optimal design for supersonic civil aircraft, a multi-fidelity optimal design program for low sonic boom is developed based on the CoKriging surrogate model combined with fast sonic boom prediction method and high fidelity sonic boom prediction method. The sonic boom prediction results of the TU-144 model are basically consistent with the experimental results, verifying the reliability of the two prediction methods. A parameter sensitivity analysis and optimal design are conducted on the wing shape of a certain supersonic civil aircraft model. The results show that Stevens′ loudness level of the ground sonic boom is more sensitive to three parameters:the half span length of the outer wing, leading edge sweep angle of the outer wing, the half span length of the inner wing. After optimization, the maximum ground sonic boom overpressure is reduced by about 4 Pa, and the Stevens′ loudness level is reduced by 4.26 dB. Compared with the Kriging model that only uses high fidelity sample data, the CoKriging model integrates high and low fidelity sample data, saving about 43% of time cost while ensuring a certain prediction accuracy. |
| format | Article |
| id | doaj-art-f4c9bf8334c54b68a2b71e06aee8f5ee |
| institution | OA Journals |
| issn | 1674-8190 |
| language | zho |
| publishDate | 2025-06-01 |
| publisher | Editorial Department of Advances in Aeronautical Science and Engineering |
| record_format | Article |
| series | Hangkong gongcheng jinzhan |
| spelling | doaj-art-f4c9bf8334c54b68a2b71e06aee8f5ee2025-08-20T02:39:03ZzhoEditorial Department of Advances in Aeronautical Science and EngineeringHangkong gongcheng jinzhan1674-81902025-06-011636069,8110.16615/j.cnki.1674-8190.2025.03.06hkgcjz-16-3-60Optimal design for low sonic boom based on CoKriging surrogate modelZHANG Hanqi0XU Yue1ZHONG Min2LI Yan3Chinese Aeronautical Establishment, Beijing 100012, ChinaChinese Aeronautical Establishment, Beijing 100012, ChinaChinese Aeronautical Establishment, Beijing 100012, ChinaChinese Aeronautical Establishment, Beijing 100012, ChinaAccurately predicting and effectively reducing sonic boom levels is one of the key issues in the development of the new generation of green supersonic civil aircraft. In order to improve the efficiency of low sonic boom optimal design for supersonic civil aircraft, a multi-fidelity optimal design program for low sonic boom is developed based on the CoKriging surrogate model combined with fast sonic boom prediction method and high fidelity sonic boom prediction method. The sonic boom prediction results of the TU-144 model are basically consistent with the experimental results, verifying the reliability of the two prediction methods. A parameter sensitivity analysis and optimal design are conducted on the wing shape of a certain supersonic civil aircraft model. The results show that Stevens′ loudness level of the ground sonic boom is more sensitive to three parameters:the half span length of the outer wing, leading edge sweep angle of the outer wing, the half span length of the inner wing. After optimization, the maximum ground sonic boom overpressure is reduced by about 4 Pa, and the Stevens′ loudness level is reduced by 4.26 dB. Compared with the Kriging model that only uses high fidelity sample data, the CoKriging model integrates high and low fidelity sample data, saving about 43% of time cost while ensuring a certain prediction accuracy.http://hkgcjz.cnjournals.com/hkgcjz/article/abstract/2023278sonic boomsurrogate modelsupersonic civil aircraftmulti-fidelityoptimal design |
| spellingShingle | ZHANG Hanqi XU Yue ZHONG Min LI Yan Optimal design for low sonic boom based on CoKriging surrogate model Hangkong gongcheng jinzhan sonic boom surrogate model supersonic civil aircraft multi-fidelity optimal design |
| title | Optimal design for low sonic boom based on CoKriging surrogate model |
| title_full | Optimal design for low sonic boom based on CoKriging surrogate model |
| title_fullStr | Optimal design for low sonic boom based on CoKriging surrogate model |
| title_full_unstemmed | Optimal design for low sonic boom based on CoKriging surrogate model |
| title_short | Optimal design for low sonic boom based on CoKriging surrogate model |
| title_sort | optimal design for low sonic boom based on cokriging surrogate model |
| topic | sonic boom surrogate model supersonic civil aircraft multi-fidelity optimal design |
| url | http://hkgcjz.cnjournals.com/hkgcjz/article/abstract/2023278 |
| work_keys_str_mv | AT zhanghanqi optimaldesignforlowsonicboombasedoncokrigingsurrogatemodel AT xuyue optimaldesignforlowsonicboombasedoncokrigingsurrogatemodel AT zhongmin optimaldesignforlowsonicboombasedoncokrigingsurrogatemodel AT liyan optimaldesignforlowsonicboombasedoncokrigingsurrogatemodel |