Reduced-Order Model for Performance Simulation and Conceptual Design of Rocket-Type Pulse Detonation Engines
A model-based method has been developed for the performance simulation and conceptual design of rocket-type pulse detonation engines (PDEs). A reduced-order model (ROM) has been generated based on the high order singular value decomposition of a data tensor obtained from CFD computations. This ROM c...
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MDPI AG
2025-02-01
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| Series: | Aerospace |
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| Online Access: | https://www.mdpi.com/2226-4310/12/2/132 |
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| author | Luis Sánchez de León Francisco Sastre Elena Martin Angel Velazquez |
| author_facet | Luis Sánchez de León Francisco Sastre Elena Martin Angel Velazquez |
| author_sort | Luis Sánchez de León |
| collection | DOAJ |
| description | A model-based method has been developed for the performance simulation and conceptual design of rocket-type pulse detonation engines (PDEs). A reduced-order model (ROM) has been generated based on the high order singular value decomposition of a data tensor obtained from CFD computations. This ROM could be used to solve the direct (performance) and inverse (design) problems in the context of the early phases of pulse detonation engine design. Output performance parameters are predicted from prescribed input operation/geometry parameters in the direct problem, and vice versa in the inverse problem. The focus of this method is industrial application in situations where large parametric searches are to be performed with a reasonable level of fidelity at a low computational cost. It was found that the performance and conceptual design tool thus developed provides results that deviate, on average, by less than 10% from the CFD results. Regarding practical implementation, the method allows for shifting the heavier computational load off-line. In this way, when working on-line, the user can obtain results in less than a second for every single case. The main contribution of this study is showing that a model-based approach that combines CFD and tensor decomposition has the potential to extract a maximum of information from a given computational effort. This characteristic makes the method of interest for early design phases in the aerospace industry. |
| format | Article |
| id | doaj-art-d66238af2eb94121b98dbc2cd74a74f0 |
| institution | DOAJ |
| issn | 2226-4310 |
| language | English |
| publishDate | 2025-02-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj-art-d66238af2eb94121b98dbc2cd74a74f02025-08-20T02:44:33ZengMDPI AGAerospace2226-43102025-02-0112213210.3390/aerospace12020132Reduced-Order Model for Performance Simulation and Conceptual Design of Rocket-Type Pulse Detonation EnginesLuis Sánchez de León0Francisco Sastre1Elena Martin2Angel Velazquez3Fluid Mechanics and Aerospace Propulsion Department, Universidad Politécnica de Madrid, 28040 Madrid, SpainFluid Mechanics and Aerospace Propulsion Department, Universidad Politécnica de Madrid, 28040 Madrid, SpainInstitute of Physics and Aerospace Sciences IFCAE, School of Aeronautics and Space Engineering, Universidad de Vigo, Campus Ourense, 36004 Ourense, SpainFluid Mechanics and Aerospace Propulsion Department, Universidad Politécnica de Madrid, 28040 Madrid, SpainA model-based method has been developed for the performance simulation and conceptual design of rocket-type pulse detonation engines (PDEs). A reduced-order model (ROM) has been generated based on the high order singular value decomposition of a data tensor obtained from CFD computations. This ROM could be used to solve the direct (performance) and inverse (design) problems in the context of the early phases of pulse detonation engine design. Output performance parameters are predicted from prescribed input operation/geometry parameters in the direct problem, and vice versa in the inverse problem. The focus of this method is industrial application in situations where large parametric searches are to be performed with a reasonable level of fidelity at a low computational cost. It was found that the performance and conceptual design tool thus developed provides results that deviate, on average, by less than 10% from the CFD results. Regarding practical implementation, the method allows for shifting the heavier computational load off-line. In this way, when working on-line, the user can obtain results in less than a second for every single case. The main contribution of this study is showing that a model-based approach that combines CFD and tensor decomposition has the potential to extract a maximum of information from a given computational effort. This characteristic makes the method of interest for early design phases in the aerospace industry.https://www.mdpi.com/2226-4310/12/2/132pulse detonation engineconceptual designperformance |
| spellingShingle | Luis Sánchez de León Francisco Sastre Elena Martin Angel Velazquez Reduced-Order Model for Performance Simulation and Conceptual Design of Rocket-Type Pulse Detonation Engines Aerospace pulse detonation engine conceptual design performance |
| title | Reduced-Order Model for Performance Simulation and Conceptual Design of Rocket-Type Pulse Detonation Engines |
| title_full | Reduced-Order Model for Performance Simulation and Conceptual Design of Rocket-Type Pulse Detonation Engines |
| title_fullStr | Reduced-Order Model for Performance Simulation and Conceptual Design of Rocket-Type Pulse Detonation Engines |
| title_full_unstemmed | Reduced-Order Model for Performance Simulation and Conceptual Design of Rocket-Type Pulse Detonation Engines |
| title_short | Reduced-Order Model for Performance Simulation and Conceptual Design of Rocket-Type Pulse Detonation Engines |
| title_sort | reduced order model for performance simulation and conceptual design of rocket type pulse detonation engines |
| topic | pulse detonation engine conceptual design performance |
| url | https://www.mdpi.com/2226-4310/12/2/132 |
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