Study on Inlet and Engine Integrated Model with Normal Shock Position Feedback
In order to consider the inlet and engine integrated model of supersonic airliner, the dynamic identification and control of inlet normal shock are studied. The research is based on the bleed air flow rate under supersonic conditions. With the two-dimensional CFD model of supersonic inlet, the dynam...
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| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
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Wiley
2020-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2020/5313941 |
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| _version_ | 1832566448064561152 |
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| author | Haoying Chen Haibo Zhang Zhihua Xi Qiangang Zheng |
| author_facet | Haoying Chen Haibo Zhang Zhihua Xi Qiangang Zheng |
| author_sort | Haoying Chen |
| collection | DOAJ |
| description | In order to consider the inlet and engine integrated model of supersonic airliner, the dynamic identification and control of inlet normal shock are studied. The research is based on the bleed air flow rate under supersonic conditions. With the two-dimensional CFD model of supersonic inlet, the dynamic and static effects of the bleeding flow rate on the normal shock position were investigated. The transfer function was identified, and simultaneously the paper carried out a comprehensive study of inlet and engine integrated model, which is established based on the inlet shock position model and engine component level model. The relationship between normal shock position and total pressure recovery coefficient has been taken into consideration in this model. Based on the inlet and engine integrated model, the closed-loop control simulation of normal shock position is carried out. The results show that the model could resist the disturbance of the inlet flow and keep the inlet and engine matching operation point stable near the optimal value. |
| format | Article |
| id | doaj-art-f0fab8107f714669952a8e7aff3d4728 |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2020-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-f0fab8107f714669952a8e7aff3d47282025-02-03T01:04:10ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742020-01-01202010.1155/2020/53139415313941Study on Inlet and Engine Integrated Model with Normal Shock Position FeedbackHaoying Chen0Haibo Zhang1Zhihua Xi2Qiangang Zheng3Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, No. 29 Yudao Street, Nanjing 210016, ChinaJiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, No. 29 Yudao Street, Nanjing 210016, ChinaJiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, No. 29 Yudao Street, Nanjing 210016, ChinaJiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, No. 29 Yudao Street, Nanjing 210016, ChinaIn order to consider the inlet and engine integrated model of supersonic airliner, the dynamic identification and control of inlet normal shock are studied. The research is based on the bleed air flow rate under supersonic conditions. With the two-dimensional CFD model of supersonic inlet, the dynamic and static effects of the bleeding flow rate on the normal shock position were investigated. The transfer function was identified, and simultaneously the paper carried out a comprehensive study of inlet and engine integrated model, which is established based on the inlet shock position model and engine component level model. The relationship between normal shock position and total pressure recovery coefficient has been taken into consideration in this model. Based on the inlet and engine integrated model, the closed-loop control simulation of normal shock position is carried out. The results show that the model could resist the disturbance of the inlet flow and keep the inlet and engine matching operation point stable near the optimal value.http://dx.doi.org/10.1155/2020/5313941 |
| spellingShingle | Haoying Chen Haibo Zhang Zhihua Xi Qiangang Zheng Study on Inlet and Engine Integrated Model with Normal Shock Position Feedback International Journal of Aerospace Engineering |
| title | Study on Inlet and Engine Integrated Model with Normal Shock Position Feedback |
| title_full | Study on Inlet and Engine Integrated Model with Normal Shock Position Feedback |
| title_fullStr | Study on Inlet and Engine Integrated Model with Normal Shock Position Feedback |
| title_full_unstemmed | Study on Inlet and Engine Integrated Model with Normal Shock Position Feedback |
| title_short | Study on Inlet and Engine Integrated Model with Normal Shock Position Feedback |
| title_sort | study on inlet and engine integrated model with normal shock position feedback |
| url | http://dx.doi.org/10.1155/2020/5313941 |
| work_keys_str_mv | AT haoyingchen studyoninletandengineintegratedmodelwithnormalshockpositionfeedback AT haibozhang studyoninletandengineintegratedmodelwithnormalshockpositionfeedback AT zhihuaxi studyoninletandengineintegratedmodelwithnormalshockpositionfeedback AT qiangangzheng studyoninletandengineintegratedmodelwithnormalshockpositionfeedback |