Design of Thermal Protection System for Reusable Hypersonic Vehicle Using Inverse Approach

Kumar, Sachin; Mahulikar, Shripad P.

doi:10.2514/1.a33688

Cited by 18 publications

(6 citation statements)

References 34 publications

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“…Differently than sticks used for thickness distribution, this additional set of primitives returns just binary values used to define specific materials. In this case the field function mth (see relation (12)) assumes a constant value equal to one inside the finite support of a stick and zero elsewhere. The parametric equations which describe material assignments are mx c, q¼1;2;3;4;5 fg ¼ 0:0;0:0;0:0;1:0;1:0 fg mz c, q¼1;…;5 with normalized parameters reported in Table 1.…”

Section: Materials Modelingmentioning

confidence: 99%

“…Therefore, a preliminary appraisal of vehicle performances is commonly performed using high-efficiency, low-order fidelity methods that give a support to a multidisciplinary analysis performed with a computational effort which fit the typical timeline of the conceptual design phase [11]. In current studies, TPS sizing is performed using several simplified assumptions, carrying out a one-dimensional heat conduction analysis with panel thickness modeled using stackups of different materials [12].…”

Section: Introductionmentioning

confidence: 99%

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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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Section: Materials Modelingmentioning

confidence: 99%

Section: Introductionmentioning

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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show abstract

“…During the service of the thermal protection structures, they will be subjected to loads such as aerodynamic force, aerodynamic heat, aerodynamic noise, and propulsion pulse force [5] . One of the main mechanical behaviors of thermal protection structures under multi-load coupling is flexural deformation.…”

Section: Introductionmentioning

confidence: 99%

Optimization of anti-bending deformation of aerogel sandwich thermal protection structure

Yang

Zhang

Tian

et al. 2022

J. Phys.: Conf. Ser.

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The failure of the thermal protection structure is very important to the safety of the aircraft structure. In order to accurately predict the flexural behavior of the aerogel sandwich thermal protection structure, first of all, for the sandwich structure in the form of statically indeterminate beam with variable cross-section, the beam theory considering the transverse shear deformation of the core layer was deduced. Secondly, by comparing the deflections, the forms of deflection curve and the maximum strains of the upper panel, the accuracy of the theoretical prediction was analyzed. Then, according to the requirements of heat protection and integrity of the thermal protection structure, the optimization analyses of the parameters of the core layer, such as the thickness, the density and the elastic modulus, were carried out. The results showed that the beam theory considering the transverse shear deformation of the core layer had better prediction accuracy. The maximum deflection error was the smallest, which was -17%, and the form of the deflection curve was the most reasonable. Within the range of the physical parameters of the core layer studied, the theoretical basis and guiding direction were given for the regulation of the performance of the aerogel core layer.

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“…The aerothermal environment is a basic design criterion for either TPS sizing or choice of materials [12,13]. TPS sizing is generally performed once the reentry trajectory is assigned, having computed the peak heating flux and the time integrated heat load [14].…”

Section: Introductionmentioning

confidence: 99%

“…Equation 18is solved using a Newton-Raphson method to determine the wall temperature T w2i on each panel of the TPS thickness discretized as shown Figure 7. The interior TPS wall temperature T w1i is computed at each node of the discrete i-th panel of the TPS integrating in time a onedimensional unsteady heat-diffusion model [12,23]. Both the initial and boundary conditions assigned as…”

mentioning

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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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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Design of Thermal Protection System for Reusable Hypersonic Vehicle Using Inverse Approach

Cited by 18 publications

References 34 publications

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

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

Optimization of anti-bending deformation of aerogel sandwich thermal protection structure

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

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