Control-oriented quasi-one dimensional modeling method for scramjet
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Zhihua Xi
Abstract
The scramjet model used in the control system needs to consider both accuracy and real-time requirements. In this paper, a quasi-one dimensional component level model method for scramjet is proposed. Under the premise of meeting the real-time requirement, this modeling method has higher calculation accuracy, and can obtain higher thrust performance without exceeding the limits. In order to improve the calculation accuracy of the scramjet model, the boundary layer correction and the interaction between shock wave and boundary layer are considered in the inlet and isolator modeling process by using reference temperature method. For the scramjet compression components, the inlet and isolator models are simplified based on shock train theory to improve real-time performance. Meanwhile, the combustor model and nozzle model are established and the combustor model is established with the combination of equal area and isothermal based on temperature limitation. Considering the boundary layer correction, the accuracy of the inlet and isolator model is improved by 8.79 and 7.9% respectively. Compared with the equal area combustion mode, the combined combustion mode can get higher thrust. In the C + + simulation environment, the average calculation time of each state point is about 25 ms which meets the real-time requirements.
Funding source: China Postdoctoral Science Foundation Funded Project
Award Identifier / Grant number: Grant 2019M661835
Funding source: National Science and Technology Major Project
Award Identifier / Grant number: Grant 2017-V-0004-0054
Funding source: Aeronautics Power Foundation
Award Identifier / Grant number: Grant 6141B09050385
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Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
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Research funding: This study is supported by National Science and Technology Major Project (Grant 2017-V-0004-0054), Aeronautics Power Foundation (Grant 6141B09050385), China Postdoctoral Science Foundation Funded Project (Grant 2019M661835).
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Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
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© 2021 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- Frontmatter
- Natural frequency analysis of a functionally graded rotor-bearing system with a slant crack subjected to thermal gradients
- Evaluation of exit pattern factors of an annular aero gas turbine combustor at altitude off-design conditions
- Research on quasi-one-dimensional modeling and performance analysis of RBCC propulsion system
- Performance characteristics of flow in annular diffuser using CFD
- Control-oriented quasi-one dimensional modeling method for scramjet
- Effect of rotor–stator rim cavity flow on the turbine
- An improved aerodynamic performance optimization method of 3-D low Reynolds number rotor blade
- Hot gas ingestion in chute rim seal clearance of gas turbine
- An improved compact propulsion system model based on batch normalize deep neural network
- Study of the vortex chamber and its application for the development of novel measurement and control devices
- Effect of equivalence ratio on the detonation noise characteristics of pulse detonation engine
- Simulation and analysis of hot plume infrared signature based on SNB model
Artikel in diesem Heft
- Frontmatter
- Natural frequency analysis of a functionally graded rotor-bearing system with a slant crack subjected to thermal gradients
- Evaluation of exit pattern factors of an annular aero gas turbine combustor at altitude off-design conditions
- Research on quasi-one-dimensional modeling and performance analysis of RBCC propulsion system
- Performance characteristics of flow in annular diffuser using CFD
- Control-oriented quasi-one dimensional modeling method for scramjet
- Effect of rotor–stator rim cavity flow on the turbine
- An improved aerodynamic performance optimization method of 3-D low Reynolds number rotor blade
- Hot gas ingestion in chute rim seal clearance of gas turbine
- An improved compact propulsion system model based on batch normalize deep neural network
- Study of the vortex chamber and its application for the development of novel measurement and control devices
- Effect of equivalence ratio on the detonation noise characteristics of pulse detonation engine
- Simulation and analysis of hot plume infrared signature based on SNB model
