A reduced order aerothermodynamic modeling framework for hypersonic vehicles based on surrogate and POD

Chen, Xin; Liu, Li; Li, Teng; Yue, Zhenjiang

doi:10.1016/j.cja.2015.06.024

Cited by 39 publications

(21 citation statements)

References 27 publications

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“…Capra et al [180] used the iterative algorithm to conduct a structural coupling of flow field, convective heat transfer, and wall temperature based on two-dimensional and three-dimensional models, which is likely to be applied to wall heat transfer in the combustion chamber of ramjets. Chen also proposed an aerodynamic modeling approach with less orders based on surrogate [181]. However, no study has been carried out on the correlation between this theory and relevant dynamical system models.…”

Section: Thermal Protection Systemsmentioning

confidence: 99%

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

et al. 2019

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Combined-cycle engine is a potential propulsion system for hypersonic aircraft. To ensure long-term, normal operation of combined-cycle engine under the harsh environment of high thermal load, it is of great significance to study the thermal protection and management of the propulsion system. In this study, the objective and development status of thermal protection and thermal management systems for the combined-cycle propulsion system were described. The latest research progresses of thermal protection, thermal barrier coating, and thermal management system of the combined-cycle propulsion system were summarized. Moreover, the problems and shortcoming in current researches were summarized. In addition, a prospect for the future development of thermal protection and management of the combined-cycle propulsion system was presented, pointing out a direction of great value and vital research significance to thermal protection and management of the combined-cycle propulsion system.

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Section: Thermal Protection Systemsmentioning

confidence: 99%

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

et al. 2019

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Section: Introductionmentioning

confidence: 99%

“…The POD is a spectral method that depends on the discrete physical space and collects the snapshots of the full-order solution that correspond to a specific input to calculate an orthogonal basis. 13 The biggest advantage of POD is that it can exploit a limited number of modes to accurately represent the fullorder system compared with other reduced-basis methods. 14 Bialecki et al 15,16 applied POD to reduce the order of linear thermal conductive systems with time-independent and time-varying loading, respectively, thereby showing that the low-order surrogate model can describe the original system.…”

Section: Introductionmentioning

confidence: 99%

Reduced-order models for radiative heat transfer of hypersonic vehicles

Yan

Jing

Yun

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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Aerothermoelastic analysis of hypersonic vehicles is a complex multidisciplinary coupling problem. Thus, accurate modeling of varying disciplines with low computational cost is necessary. This work developed a tractable approach-based reduced-order modeling technology to solve the radiative thermal transfer problem in a hypersonic simulation. A method that combines proper orthogonal decomposition and unassembled discrete empirical interpolation method is developed to construct the reduced-order modeling. First, high-dimensional original systems are projected on the optional basis generated by proper orthogonal decomposition, and the nonlinear term is further approximated by unassembled discrete empirical interpolation method. Then, a numerical integration method for the solution of the reduced system of nonlinear differential equations is provided. Case studies that use a classical hypersonic control surface model, in which the time history and spatial distribution of the thermal load are known a priori, are conducted to validate the accuracy and efficiency of the reduced-order modeling methodology and to assess the robustness of the reduced-order modeling for thermal solution. Results indicate the ability of reduced-order modeling to reduce the nonlinear system size with reasonable accuracy.

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“…An alternative approach is to use reduced-order models (ROMs) [10][11][12] that are derived from high-fidelity analysis tools. Chen et al [13] provided a computationally efficient and accurate ROM framework based on surrogate and proper orthogonal decomposition (POD) for incorporating aerodynamic heating into a coupled aerothermoelastic analysis. Based on the basis augmentation and surrogate modeling techniques, Falkiewicz and Cesnik [14] proposed a reduced-order aerothermoelastic simulation framework to improve the computational efficiency.…”

Section: Introductionmentioning

confidence: 99%

Aerothermoelastic Analysis of a Hypersonic Vehicle Based on Thermal Modal Reconstruction

Chen

Zhao

2019

International Journal of Aerospace Engineering

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Hypersonic vehicles operate in a severe aerodynamic heating environment, which has a significant impact on their structural dynamic characteristics. Therefore, aerodynamic heating effects cannot be ignored when performing an aeroelastic analysis for a hypersonic vehicle. However, incorporating aerodynamic heating effects into the fluid-structural coupling analysis will result in extreme computational costs. Actually, after experiencing a sustained flight in a fixed state, the vehicle will eventually reach the thermodynamic equilibrium. Thus, the aeroelastic analysis can be efficiently performed by using the structural dynamic characteristics of the heated vehicle operating in each equilibrium state. The effects of aerodynamic heating show that the modal frequencies and modal shapes of the flexible structure are bound to change significantly in comparison with the unheated structure. In this paper, a method of thermal modal reconstruction is developed in order to directly generate the structural mode shapes and frequencies within the given parameter space without having to solve a high-fidelity thermal and structural problem. Once the modal data are available, the multivariate interpolation in a tangent space to Grassmann manifold is used to generate the modal matrix at the arbitrary selected parameter point. Besides, the Kriging interpolation method is used to establish the approximate relationships between natural frequencies and sampling points. Finally, an example of an aerodynamic heated control surface structure is used to validate the effectiveness of the proposed aerothermoelastic framework. It is demonstrated that the developed thermal modal reconstruction method has good robustness, very high computational efficiency, and sufficient accuracy over a wide parametric domain.

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A reduced order aerothermodynamic modeling framework for hypersonic vehicles based on surrogate and POD

Cited by 39 publications

References 27 publications

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

Reduced-order models for radiative heat transfer of hypersonic vehicles

Aerothermoelastic Analysis of a Hypersonic Vehicle Based on Thermal Modal Reconstruction

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