Free Form Deformation Method Applied to Modeling and Design of Hypersonic Glide Vehicles

Zhang, Bin; Feng, Zhiwei; Xu, Boting; Yang, Tao

doi:10.1109/access.2019.2915516

Cited by 7 publications

(5 citation statements)

References 32 publications

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“…Discretization and physical model errors stem from hardware limitations and current constraints in physical mechanism research (Zhang et al , 2019). Conversely, empirical errors arise from the application of unsuitable grid strategies and turbulence models.…”

Section: Numerical Error Based On Finite Volume Methodsmentioning

confidence: 99%

Research on precise and standardized numerical simulation strategy for vehicle aerodynamics

Chen,

Liu,

et al. 2024

HFF

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Purpose The purpose of this study is to propose a precise and standardized strategy for numerically simulating vehicle aerodynamics. Design/methodology/approach Error sources in computational fluid dynamics were analyzed. Additionally, controllable experiential and discretization errors, which significantly influence the calculated results, are expounded upon. Considering the airflow mechanism around a vehicle, the computational efficiency and accuracy of each solution strategy were compared and analyzed through numerous computational cases. Finally, the most suitable numerical strategy, including the turbulence model, simplified vehicle model, calculation domain, boundary conditions, grids and discretization scheme, was identified. Two simplified vehicle models were introduced, and relevant wind tunnel tests were performed to validate the selected strategy. Findings Errors in vehicle computational aerodynamics mainly stem from the unreasonable simplification of the vehicle model, calculation domain, definite solution conditions, grid strategy and discretization schemes. Using the proposed standardized numerical strategy, the simulated steady and transient aerodynamic characteristics agreed well with the experimental results. Originality/value Building upon the modified Low-Reynolds Number k-e model and Scale Adaptive Simulation model, to the best of the authors’ knowledge, a precise and standardized numerical simulation strategy for vehicle aerodynamics is proposed for the first time, which can be integrated into vehicle research and design.

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Section: Numerical Error Based On Finite Volume Methodsmentioning

confidence: 99%

Research on precise and standardized numerical simulation strategy for vehicle aerodynamics

Chen,

Liu,

et al. 2024

HFF

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show abstract

“…Taking the typical windward side in Fig. 1 as an example, we take a border-based FFD control surface [17] to replace the traditional FFD control lattice in this paper. The border-based FFD control surface takes the projected edge of the windward side as the boundary of the control lattice, as shown in Fig.…”

Section: B Ffd Modeling Of the Windward Sidementioning

confidence: 99%

“…4. As an irregular control lattice, the border-based FFD control surface is geometrically consistent with the to-be-deformed windward side, so it can improve operational efficiency and geometric continuity [17].…”

Section: B Ffd Modeling Of the Windward Sidementioning

confidence: 99%

Efficient Aerodynamic Shape Optimization of the Hypersonic Lifting Body Based on Free Form Deformation Technique

Zhang

Feng

et al. 2019

IEEE Access

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Aerodynamic shape optimization (ASO) of hypersonic lifting body has become a significant research topic due to its significant performance advantages. As a universal parameterization, the free form deformation (FFD) technique has benefits including geometric independence, random deformation, and mesh synchronization. In this paper, an effective design method to apply the FFD technique in the ASO of a hypersonic lifting body is presented. Some commonly used basis functions are researched in FFD modeling of the windward side of a typical lifting body, including the Bernstein polynomial, the B-spline function, and the non-uniform rational B-spline (NURBS) function. An efficient aerodynamic simulation method combining Euler equations (non-viscous component) and skin friction drag (viscous component based on the compressible turbulence model) is then developed to minimize computational requirements. The accuracy of the proposed method is validated, and a significant decrease in processing time is observed. In addition, a kriging surrogate model combined with infilling sampling expected improvement (EI) criterion is developed to improve optimization efficiency. To obtain a lifting body with high lift-to-drag ratio that satisfies inner loading constraint, a baseline is optimized by manipulating its shape using the NURBS-based FFD technique. The results show that the optimal shape displays outstanding aerodynamic performance, and the effective design method can provide practical support for ASO of the hypersonic lifting body.

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“…18,19 The displacement of each control point that contributes the shape deformation were naturally the design variables. [20][21][22] Variations of FFD approaches include B-spline-based FFD, 23,24 grid-based FFD, 12,21 CAD-based FFD, 25,26 etc.…”

Section: Introductionmentioning

confidence: 99%

An approach of Proper Orthogonal Decomposition-aided Free-form Deformation with application in compressor blade design

Wang

Qin

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Compressor blade design influences aero-engine performance mainly through its total pressure ratio and efficiency. As a volume-based geometric parameterization, Free-form Deformation (FFD) brings three-dimensionality that is essential to blade design. However, the manipulation of control points with respect to simple numeric parametric perturbation renders the use of design space low-efficient. Therefore, an improved FFD with ‘wiser’ control point lay-out is expected to identify those more important design variables. This paper proposes novel design variables that are assigned to grouping of control points’ displacement in FFD lay-out. In short, the approach is realized as: (i) establish a library of sufficient blade shape samples; (ii) filter the database with geometric constraints; (iii) extract dominant modes via (POD) Proper Orthogonal Decomposition; (iv) construct new design variables and apply them in optimization. With geometric constraint filtering, problem-oriented information is injected. With POD, the dominance of new selected geometric parameters in problem description is assured. Perfunctory details of displacement data of each control point in the lay-out can be replaced by grouped data as new design variable candidates. As a proof-of-concept study of the new approach, compressor blade Rotor 37 is selected to be the good platform of testing the feasibility of POD-aided FFD as a global and flexible yet economic geometric parameterization. Result demonstrates the feasibility of proposed POD-aided FFD approach that helps conduct an optimization involving displacement of 6 × 4 × 3 control points with as few as five new design variables, while still being capable of bringing optimization effect in three test cases.

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Free Form Deformation Method Applied to Modeling and Design of Hypersonic Glide Vehicles

Cited by 7 publications

References 32 publications

Research on precise and standardized numerical simulation strategy for vehicle aerodynamics

Research on precise and standardized numerical simulation strategy for vehicle aerodynamics

Efficient Aerodynamic Shape Optimization of the Hypersonic Lifting Body Based on Free Form Deformation Technique

An approach of Proper Orthogonal Decomposition-aided Free-form Deformation with application in compressor blade design

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