Multi-objective optimization for re-entry spacecraft conceptual design using a free-form shape generator

Viviani, Antonio; Iuspa, Luigi; Aprovitola, Andrea

doi:10.1016/j.ast.2017.09.030

Cited by 32 publications

(15 citation statements)

References 12 publications

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“…In the present work, we assume that the generic shape of an RLV is represented by a grid formed by a quadrangular and/or by a degenerated triangular panel grid. Grid points are obtained using a proprietary procedure that authors fully detailed in [23,24]. Without going into details of the shape model, we remark that the mesh arrangement over the RLV surface is obtained with no NURBS support surface: a three-dimensional parametric wireframe is created using cubic rational B-splines and used to reconstruct the computational surface grid.…”

Section: Rlv Shape Modelling and Thermal Protection System Sizing Crimentioning

confidence: 99%

“…The above considerations ensure a topologically invariant shape. In previous papers proposed by the authors [23,24], a multidisciplinary shape optimization for an RLV comprising a trajectorybased TPS sizing procedure was developed. The TPS was modeled using two insulating materials placed at different locations along the vehicle surface.…”

Section: Rlv Shape Modelling and Thermal Protection System Sizing Crimentioning

confidence: 99%

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Thermal Protection System Design of a Reusable Launch Vehicle Using Integral Soft Objects

Aprovitola

Iuspa

Viviani

2019

International Journal of Aerospace Engineering

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In the present paper, a modelling procedure of the thermal protection system designed for a conceptual Reusable Launch Vehicle is presented. A special parametric model, featuring a scalar field irradiated by a set of bidimensional soft objects, is developed and used to assign an almost arbitrary distribution of insulating materials over the vehicle surface. The model fully exploits the autoblending capability of soft objects and allows a rational distribution of thermal coating materials using a limited number of parameters. Applications to different conceptual vehicle configurations of an assigned thickness map, and material layout show the flexibility of the model. The model is finally integrated in the framework of a multidisciplinary analysis to perform a trajectory-based TPS sizing, subjected to fixed thermal constraints.

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Section: Rlv Shape Modelling and Thermal Protection System Sizing Crimentioning

confidence: 99%

Section: Rlv Shape Modelling and Thermal Protection System Sizing Crimentioning

confidence: 99%

Thermal Protection System Design of a Reusable Launch Vehicle Using Integral Soft Objects

Aprovitola

Iuspa

Viviani

2019

International Journal of Aerospace Engineering

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“…A generic shape of an RLV is represented by a grid formed by a quadrangular and/or by either degenerated triangular panel grid. Grid points are obtained using a proprietary procedure that authors fully detailed in [20,21]. Without going into details of the shape model, we remark that the mesh arrangement over the RLV surface is obtained with no NURBS support surface: a three-dimensional parametric wireframe is created using cubic rational B-splines [22] and used to reconstruct computational surface grid.…”

Section: Rlv Shape Modelingmentioning

confidence: 99%

“…The previously introduced modeling procedure has been applied on a conceptual RLV shape created with the model described in Section 4 and detailed in [20,21]. Figure 6 shows a topological map obtained for an arbitrarily chosen distribution of stick primitives.…”

Section: Tps Modeling Capabilitiesmentioning

confidence: 99%

Parametric Integral Soft Objects-based Procedure for Thermal Protection System Modeling of Reusable Launch Vehicle

Aprovitola¹,

Iuspa²,

Viviani³

2019

Hypersonic Vehicles - Past, Present and Future Developments

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The present paper deals with a modeling procedure of a thermal protection system (TPS) designed for a conceptual reusable launch vehicle (RLV). A novel parametric model based on a scalar field created by a set of soft object primitives is used to assign an almost arbitrary seamless distribution of insulating materials over the vehicle surface. Macroaggregates of soft objects are created using suitable geometric supports allowing a distribution of coating materials using a limited number of parameters. Applications to different conceptual vehicle configurations of an assigned thickness map and materials layout show the flexibility of the model.

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“…Yang et al [10] investigate the stress-constrained topology optimization based on maximum stress measures that give beneficial information about an easy implementation, low computational cost, and stable converge topology optimization process. Viviani et al [11] use multi-objective structural topology optimization for turbine brake pads subject to thermal and brake vibration. The result of the study shows that the optimized structure meets the stiffness requirement, as well as improves vibration performance.…”

Section: Introductionmentioning

confidence: 99%

Topology and Response Surface Optimization of a Bicycle Crank Arm with Multiple Load Cases

Ismail

Koo

2020

Applied Sciences

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This paper presents an application of topology optimization and response surface method to optimize the geometry of a bicycle crank arm and the experimental validation of it. This is purposely to reduce the crank arm mass and create a preliminary design of a lightweight structure necessary for the high-performance bicycle development. A three-dimensional bike crank arm model was made in the SpaceClaim software followed by a static finite element analysis using ANSYS Workbench 2019 R1. A multiple cycling load was applied simultaneously in seven crank angles of 30, 45, 60, 90, 120, 135, and 150° relative to the horizontal position to create the multiple loads to the crank. From there, topology optimization was then conducted to investigate the effect of mass constraint, stress constraint, angle of cycling, and crank materials on the topological pattern result. To minimize stress concentration at corners, a shape optimization using the response surface method was conducted and obtained the final geometry. From the result, it is shown that both optimization methods not only successfully reduce the crank arm mass and provide several optimum design options but also are able to reduce the maximum stress in the crank arm up to 20% after the optimization process. The experimental validation using a newly developed wireless measurement system shows a considerable agreement to the numerical results.

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Multi-objective optimization for re-entry spacecraft conceptual design using a free-form shape generator

Cited by 32 publications

References 12 publications

Thermal Protection System Design of a Reusable Launch Vehicle Using Integral Soft Objects

Thermal Protection System Design of a Reusable Launch Vehicle Using Integral Soft Objects

Parametric Integral Soft Objects-based Procedure for Thermal Protection System Modeling of Reusable Launch Vehicle

Topology and Response Surface Optimization of a Bicycle Crank Arm with Multiple Load Cases

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