Prediction of temperature variation in a rotating spacecraft in space environment

Gadalla, Mohamed

doi:10.1016/j.applthermaleng.2004.12.018

Cited by 26 publications

(22 citation statements)

References 15 publications

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“…(24) was determined from the mixed type boundary condition of Eq. (15) and a special treatment of the boundary conditions as indicated by Gadalla [31].…”

Section: Methods Of Solutionmentioning

confidence: 99%

“…The analytical solution in Gadalla [31] indicates that large temperature variations may occur in the spacecraft, especially at low rotational speeds. Hence, to accurately simulate the temperature field, a uniformly distributed fine grid of 400 × 200 points, in the angular and radial directions respectively, is adopted in the present study.…”

Section: Methodsmentioning

confidence: 99%

“…The first term on the right‐hand side of the previous equation is not convenient for analytical treatment, but it can be replaced by an equivalent expression through Fourier analysis where G n are the coefficients that were determined as indicated by Gadalla [31] such that: Using Eq. (24) for \documentclass{article}\usepackage{amsmath}\usepackage{amssymb}\usepackage{amsbsy}\usepackage{amsfonts}\pagestyle{empty}\begin{document}$\tilde{T}(\eta, \phi)$\end{document}, and Eq.…”

Section: Linearized Analytical Solutionmentioning

confidence: 99%

“…(27) for G n , the boundary condition of Eq. (25) becomes After separating the terms involving ϕ from the others and performing the required transformation, the general approximate analytical solution for the linearized boundary conditions is: where or and where b n was determined as indicated by Gadalla [31].…”

Section: Linearized Analytical Solutionmentioning

confidence: 99%

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Computational modeling and analysis of thermal characteristics of a rotating spacecraft subjected to solar radiation

Gadalla

Wahba

2011

Heat Trans. Asian Res.

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This paper presents a computational modeling for the temperature distribution of a rotating thick-walled cylindrical spacecraft subjected to solar radiation. The inner surface of the spacecraft is thermally insulated while the outer surface is subjected to concurrent events of solar incidence and radiative heat dissipation to space. The governing equation for the normalized temperature is discretized using a finite difference scheme and Successive Line Over-Relaxation (SLOR) is used to solve the resulting system of algebraic equations. Numerical simulations of temperature distribution on the spacecraft for different spinning speeds, angular positions, and different radii are discussed and evaluated for both linearized and nonlinear boundary conditions. Comparative analysis between the computational modeling and the exact analytical solution for the linearized boundary condition is presented. The results indicate that the outer surface temperature distribution of the spacecraft is nearly independent of the angular position; at sub-cylindrical surface, this independence is achieved at low angular velocity. Moreover, numerical simulations show that the use of the linearized boundary condition at the outer surface presents a good approximation for the case of high-speed spinning spacecrafts, while it results in significant errors in the temperature field in the case of stationary and low-speed spinning spacecrafts.

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“…(24) was determined from the mixed type boundary condition of Eq. (15) and a special treatment of the boundary conditions as indicated by Gadalla [31].…”

Section: Methods Of Solutionmentioning

confidence: 99%

Section: Methodsmentioning

confidence: 99%

Section: Linearized Analytical Solutionmentioning

confidence: 99%

Section: Linearized Analytical Solutionmentioning

confidence: 99%

See 2 more Smart Citations

Computational modeling and analysis of thermal characteristics of a rotating spacecraft subjected to solar radiation

Gadalla

Wahba

2011

Heat Trans. Asian Res.

Self Cite

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“…For instance, Oshima and Oshima [2] tried to deal with the problem but the results were not easy to apply mainly due to the parameters used and the complexity of the necessary calculations. More recently, Arduini et al [3] presented a new approach for solving the inverse problem by means of linearized techniques and Gadalla [4] studied analytically the temperature in a rotating cylindrical spacecraft.…”

Section: Introductionmentioning

confidence: 99%

Analytical study of the thermal behaviour and stability of a small satellite

Pérez-Grande¹,

Sanz-Andrés²,

Guerra³

et al. 2009

Applied Thermal Engineering

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In this work the thermal analysis of a small satellite orbiting around the Earth has been approached by direct integration of the heat balance equations of a two-node reduced model, obtaining a linearized sec-ond order ODE problem, similar in form to the classical case of the forced vibration of a damped system. As the thermal loads (solar radiation, albedo, etc.) are harmonic, the problem is solved by means of Fou-rier analysis methods. Research on that field can be directly applied to the analysis of thermal problems and the results obtained are satisfactory. Working on the frequency domain streamlines the analysis, simplifies the study and facilitates the experimental testing. The transfer functions are obtained for the two-node case but the study can be extended to an n-node model.

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Heat Transfer Model of a Small Size Satellite on Geostationary Orbit in Cold Condition

Preumont

Szewczyk

Wittels

et al. 2019

Advances in Intelligent Systems and Computing

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Prediction of temperature variation in a rotating spacecraft in space environment

Cited by 26 publications

References 15 publications

Computational modeling and analysis of thermal characteristics of a rotating spacecraft subjected to solar radiation

Computational modeling and analysis of thermal characteristics of a rotating spacecraft subjected to solar radiation

Analytical study of the thermal behaviour and stability of a small satellite

Heat Transfer Model of a Small Size Satellite on Geostationary Orbit in Cold Condition

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