Zijun Yi¹, Dan Xie^2,*

The International Conference on Computational & Experimental Engineering and Sciences, Vol.30, No.2, pp. 1-1, 2024, DOI:10.32604/icces.2024.012704

Abstract Hypersonic aircraft face complex aerodynamic forces and severe aerothermal issues. While aerodynamic and aerothermal empirical solutions exhibit high computational efficiency, they lack precision. Numerical approaches equipped with accuracy but come with high computational costs. To address the contradiction between precision and efficiency, some research on hypersonic unsteady aerodynamic and aerothermal Reduced Order Models (ROMs) was conducted in this study, using Kriging surrogate method.
Meanwhile, hypersonic aircraft typically feature numerous thin-wall structures. The strong coupling of aerodynamic, aerothermal, and elasticity will inevitably lead to aerothermoelastic effects. This study centered on the Thermal Protection System (TPS) panel… More >

Dan Xie^1,*, Shihao Zhang¹, Zijun Yi¹

The International Conference on Computational & Experimental Engineering and Sciences, Vol.26, No.1, pp. 1-1, 2023, DOI:10.32604/icces.2023.010490

Abstract Considering the high cost of numerical simulation for aeroelastic coupling analysis, it is difficult to directly apply it to engineering. In this paper, the typical swept trapezoidal wing of hypersonic aircraft [1] is simplified to a cantilever trapezoidal plate [2]. Based on semi-analytical method [3], including von Karman plate theory to consider the structural geometric nonlinearity, third-order piston theory to calculate quasi steady aerodynamic force, and Rayleigh-Ritz method to characterize the displacement as a mode superposition form, the aeroelastic equation of the swept trapezoidal wing is established, and the fourthorder Runge Kutta numerical integration is More >

Javed S. Shaikh^1,*, Krishna Kumar¹, Khizar A. Pathan², Sher A. Khan³

FDMP-Fluid Dynamics & Materials Processing, Vol.19, No.6, pp. 1637-1653, 2023, DOI:10.32604/fdmp.2023.025113 - 30 January 2023

Abstract The complex fluid-dynamic instabilities and shock waves occurring along the surface of a two-dimensional wedge at high values of the Mach number are studied here through numerical solution of the governing equations. Moreover, a regression model is implemented to determine the pressure distribution for various Mach numbers and angles of incidence. The Mach number spans the interval from 1.5 to 12. The wedge angles (θ) are from 5° to 25°. The pressure ratio (P₂/P₁) is reported at various locations (x/L) along the 2D wedge. The results of the numerical simulations are compared with the regression model More >

Chunxiu Ji¹, Dan Xie^1,*

The International Conference on Computational & Experimental Engineering and Sciences, Vol.24, No.1, pp. 1-2, 2022, DOI:10.32604/icces.2022.08737

Abstract This study has established a reduced order model (ROM) based on spectral proper orthogonal decomposition (SPOD) method in order to proceed an aerothermoelastic response analysis of a hypersonic panel. The two-way coupling between aerothermal and aeroelastic systems is applied [1]. Three aspects of POD-ROM are investigated: 1) the selection of snapshots for POD modes; 2) the comparison between classical POD [2] and SPOD [3]; 3) how to find global POD modes in a parameter space of flight altitude and Mach number. The snapshots are sampled from aerothermoelastic response data via the classical Galerkin method. The… More >

Antonio Esposito¹, Marcello Lappa^2,*, Rocco Pagliara³, Gennaro Spada¹

FDMP-Fluid Dynamics & Materials Processing, Vol.18, No.2, pp. 189-203, 2022, DOI:10.32604/fdmp.2022.019605 - 16 December 2021

Abstract The ability to measure the very high heat fluxes that typically occur during the hypersonic re-entry phase of space vehicles is generally considered a subject of great importance in the aerospace field. Most of the sensors used for these measurements need to be checked periodically and re-calibrated accordingly. Another bottleneck relates to the need to procure thermal sources that are able to generate reliable reference heat fluxes in the range between 100 and 1000 kW/m² (as order of magnitude). In the present study, a method is presented by which, starting from a calibration system with a capacity… More >

Kai Liu^{1, 2}, Zheng Hou^{2, *}, Zhiyong She², Jian Guo²

CMES-Computer Modeling in Engineering & Sciences, Vol.122, No.1, pp. 131-148, 2020, DOI:10.32604/cmes.2020.08124 - 01 January 2020

Abstract This paper studies the reentry attitude tracking control problem for hypersonic vehicles (HSV) equipped with reaction control systems (RCS) and aerodynamic surfaces. The attitude dynamical model of the hypersonic vehicles is established, and the simplified longitudinal and lateral dynamic models are obtained, respectively. Then, the compound control allocation strategy is provided and the model predictive controller is designed for the pitch channel. Furthermore, considering the complicated jet interaction effect of HSV during RCS is working, an improved model predictive control approach is presented by introducing the online parameter estimation of the jet interaction coefficient for More >

R.V. Reji, S. Anil Lal^†

Frontiers in Heat and Mass Transfer, Vol.7, pp. 1-8, 2016, DOI:10.5098/hmt.7.27

Abstract DSMC simulation of re-entry of an object with shape and size close to that of ISRO’s Space Recovery Experiment (SRE) capsule has been analysed using the open-source tool dsmcFoam for three altitude conditions, viz. 85 km, 100 km and 115 km, and for three angles of attack, viz. 0 o , 20o&40o . The hypersonic free stream velocity of 8000 m/s and boundary surface temperature of 300 K have been used for the simulations. The variation of parameters such as surface heat flux, surface pressure, shear stress, slip velocity, temperature jump and integrals such as More >

P. Pasolini^1,2, R. Savino¹, F. Franco¹, S. De Rosa¹

FDMP-Fluid Dynamics & Materials Processing, Vol.11, No.3, pp. 301-324, 2015, DOI:10.3970/fdmp.2015.011.301

Abstract The aim of the present work is to provide a first attempt to set an aero-thermo-elastic methodology for deployable atmospheric re-entry decelerators operating at high Mach number and high dynamic pressure. Because of the severity of re-entry conditions such as high temperatures, high pressures and high velocities, the behavior of their flexible structures is a hard target to assess. In this paper a partitioned Fluid Structure Interaction (FSI) approach based on the integration of different commercial software (STAR-CCM+ and ABAQUS) is presented. In order to validate the specific codes and the overall strategy for structural More >

V. Carandente¹, R. Savino¹, M. Iacovazzo¹, C. Boffa

FDMP-Fluid Dynamics & Materials Processing, Vol.9, No.4, pp. 461-484, 2013, DOI:10.3970/fdmp.2013.009.461

Abstract The article deals with the aerothermal analysis of a sample-return hypersonic capsule reentering on Earth from an interplanetary exploration mission. The main objective of the work is to estimate the heat flux distribution on the capsule surface and to perform one-dimensional thermal analyses for its ablative heat shield. After a short review of sample-return missions, the numerical models implemented are described and the computational results, obtained along a feasible reentry trajectory, are presented and discussed. Particular attention has been paid to compare the convective stagnation point heat fluxes obtained by means of Computational Fluid Dynamic More >

R. Savino¹, V. Carandente¹

FDMP-Fluid Dynamics & Materials Processing, Vol.8, No.4, pp. 453-476, 2012, DOI:10.3970/fdmp.2012.008.453

Abstract A new small recoverable re-entry capsule with deployable heat shield is analyzed. The possible utilization of the capsule is for safe Earth return of science payloads or data from low Earth orbit at an inexpensive cost, taking advantage of its deployable structure to perform an aerobraking re-entry mission, with relatively low heat and mechanical loads. The system concept for the heat shield is based on umbrella-like frameworks and existing ceramic fabrics. An aerothermodynamic analysis is developed to show that the peak heat flux, for a capsule with a ballistic coefficient lower than 10 kg/m², is in More >