Development of an in-house computer code for the thermal analysis of satellites using Thermal Network Method and Method of Lines

Uygur, A. Bilge; Isik, H. Gurguc; Solakoglu, Erhan; Yazıcıoğlu, Almıla G.

doi:10.1109/rast.2009.5158247

Cited by 4 publications

(7 citation statements)

References 2 publications

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“…The heat dissipation values for these components are tabulated in Table 1. [5], hot and cold extreme temperatures for an ADCU type equipment are +50 °C and -20 °C, respectively. …”

Section: Tested Devicementioning

confidence: 99%

Numerical and experimental investigation of the thermal behavior of a newly developed attitude Determination Control Unit in a Vacuum environment

Ömür

Uygur

Isik

et al. 2011

Proceedings of 5th International Conference on Recent Advances in Space Technologies - RAST2011

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Within the framework of satellite programs carried out in Turkish Aerospace Industries, Inc. (TAI), a new Attitude Determination Control Unit (ADCU) has been developed. The present study involves the Thermal Vacuum Cycling Tests (TVCT) performed on the ADCU and the thermal mathematical model developed in order to assess the thermal behavior of the equipment under vacuum environment. For the qualification of the ADCU, 8 cycles of TVCT has been performed in a ThermalVacuum Chamber (TVC). By demonstrating that the functional performance of the ADCU lies within required limits, it was shown that the ADCU is a space-qualified equipment. In addition to this, a thermal mathematical model representing the ADCU and the thermal test environment are developed using THERMICA software and simulations based on this model are carried out by SINDA/G software. Transient and steady-state predictions obtained with the software are compared with the test measurements and a good agreement was observed. Based on this agreement, it is concluded that the mathematical model employed in the present study produces accurate results for the thermal behavior of the ADCU and it is an efficient tool which can be used in the design phases of future equipment with similar properties.

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“…The heat dissipation values for these components are tabulated in Table 1. [5], hot and cold extreme temperatures for an ADCU type equipment are +50 °C and -20 °C, respectively. …”

Section: Tested Devicementioning

confidence: 99%

Numerical and experimental investigation of the thermal behavior of a newly developed attitude Determination Control Unit in a Vacuum environment

Ömür

Uygur

Isik

et al. 2011

Proceedings of 5th International Conference on Recent Advances in Space Technologies - RAST2011

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“…The code is based on Thermal Network Method (TNM) [1] in conjunction with Method of Lines (MOL) [2] for the solution of energy equation. In a previous study [3], the code was applied to a simple test problem and the results were compared with the predictions of a commercial software package (Thermica-SINDA/G [4]) on the same test problem. Excellent agreement between the two sets of results was obtained.…”

Section: Introductionmentioning

confidence: 99%

The thermal analysis of a satellite by an in-house computer code based on Thermal Network Method and Monte Carlo Ray Tracing Technique

Isik

Uygur

Ömür

et al. 2011

Proceedings of 5th International Conference on Recent Advances in Space Technologies - RAST2011

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In this paper, the development of an in-house computer code for the thermal analysis of satellites is discussed. The code is based on Thermal Network Method (TNM) in conjunction with Method of Lines (MOL) for the solution of energy equation. The view factors required for the computation of radiative exchange factors which are used in TNM are calculated by a newly developed module based on Monte-Carlo Ray Tracing Technique. The predictive accuracy of the code including the new module was assessed on a realistic test problem involving a satellite orbiting the earth at an altitude of 700 km. Comparison of transient results obtained by the in-house code and a commercial thermal analysis software package (Thermica-SINDA/G) has shown that the in-house code predictions mimic the ones obtained by Thermica-SINDA/G very accurately.

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“…Currently, there are three categories of models that are prevalently used in spacecraft thermal design: general thermal analytical models, approximate thermal analytical models [4,5], and heuristic models [6][7][8]. In general, thermal analytical models, which are the discretized form of the governing partial differential equations for heat transfer, provide detailed and accurate temperature distributions in the spacecraft that can be used to resolve the thermal interaction with other physics for coupled analysis.…”

mentioning

confidence: 99%

Projection-Based Reduced-Order Modeling for Spacecraft Thermal Analysis

Qian¹,

Wang²,

Song³

et al. 2015

Journal of Spacecraft and Rockets

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This paper presents a mathematically rigorous, subspace projection-based reduced-order modeling methodology and an integrated framework to automatically generate reduced-order models for spacecraft thermal analysis. Two key steps in the reduced-order modeling procedure are described: first, the acquisition of a full-scale spacecraft model in the ordinary differential equation, and differential algebraic equation, forms to resolve its dynamic thermal behavior; and second, reduced-order modeling to markedly reduce the dimension of the full-scale model. Specifically, proper orthogonal decomposition in conjunction with a discrete empirical interpolation method and trajectory piecewise-linear methods are developed to address the strong nonlinear thermal effects due to coupled conductive and radiative heat transfer in the spacecraft environment. Case studies using NASA-relevant satellite models are undertaken to verify the capability and to assess the computational performance of the reduced-order modeling technique in terms of speedup and error relative to the full-scale model. Reduced-order modeling exhibits excellent agreement in spatiotemporal thermal profiles (less than 0.5% relative error in pertinent timescales) along with salient computational acceleration (up to two orders of magnitude speedup) over the full-scale analysis. These findings establish the feasibility of reduced-order modeling to perform rational and computationally affordable thermal analysis, develop reliable thermal control strategies for spacecraft, and greatly reduce the development cycle times and costs. Nomenclature A = conduction exchange matrices C = thermal capacitance matrix D = scatter matrix of thermal loads Q = heat flux R = radiation exchange matrices T = temperature vector, K t = time, s U = projection space u = independent thermal inputs Subscripts r = quantity in reduced dimension space s = thermal links between the nodes and the isothermal objects t = time-varying quantity

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Development of an in-house computer code for the thermal analysis of satellites using Thermal Network Method and Method of Lines

Cited by 4 publications

References 2 publications

Numerical and experimental investigation of the thermal behavior of a newly developed attitude Determination Control Unit in a Vacuum environment

Numerical and experimental investigation of the thermal behavior of a newly developed attitude Determination Control Unit in a Vacuum environment

The thermal analysis of a satellite by an in-house computer code based on Thermal Network Method and Monte Carlo Ray Tracing Technique

Projection-Based Reduced-Order Modeling for Spacecraft Thermal Analysis

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