Overview of Satellite Thermal Analytical Model

Tsai, Jih-Run

doi:10.2514/1.9273

Cited by 58 publications

(42 citation statements)

References 1 publication

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…Note that Q i includes heat sources from internal heat generation (e.g., heaters and electronics heat dissipation) as well as environmental fluxes (e.g., direct solar radiation, albedo, and Earth radiation) [5]; K ij and R ij , are, respectively, the conductive and radiative links between nodes. N i and M i are, respectively, the numbers of the neighboring nodes interacting with the ith node via conduction and radiation.…”

Section: A Acquisition Of Full-scale Thermal Modelsmentioning

confidence: 99%

“…In contrast, approximate models based on the lumped-parameter assumption allow fast simulation speed and the ability to interrogate critical physics by parametric, tradeoff, and interface studies at an early stage of the thermal design when the spacecraft concept, structure, and test arrangement are yet to be fully defined. Therefore, it provides valuable information about the feasibility of the spacecraft from the thermal perspective [5]. However, approximate models are generally poor in accuracy and lack quantitative predictive capability.…”

mentioning

confidence: 99%

“…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%

See 2 more Smart Citations

Projection-Based Reduced-Order Modeling for Spacecraft Thermal Analysis

Qian¹,

Wang²,

Song³

et al. 2015

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

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

show abstract

Section: A Acquisition Of Full-scale Thermal Modelsmentioning

confidence: 99%

mentioning

confidence: 99%

mentioning

confidence: 99%

See 1 more Smart Citation

Projection-Based Reduced-Order Modeling for Spacecraft Thermal Analysis

Qian¹,

Wang²,

Song³

et al. 2015

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

show abstract

“…The differential equations for energy balance are nonlinear due to the presence of radiation couplings, which follow the Stefan-Boltzmann quartic law. A common approach to these equations involves a linearization of the radiation terms that approximate them by heat conduction terms [3,[5][6][7]. This approach transforms the nonlinear equations into standard linear heat conduction equations.…”

Section: Introductionmentioning

confidence: 99%

Linear Approach to the Orbiting Spacecraft Thermal Problem

Gaite¹,

Fernández-Rico²

2012

Journal of Thermophysics and Heat Transfer

View full text Add to dashboard Cite

A linear method is developed for solving the nonlinear differential equations of a lumped-parameter thermal model of a spacecraft moving in a closed orbit. This method, based on perturbation theory, is compared with heuristic linearizations of the same equations. The essential feature of the linear approach is that it provides a decomposition in thermal modes, like the decomposition of mechanical vibrations in normal modes. The stationary periodic solution of the linear equations can be alternately expressed as an explicit integral or as a Fourier series. This method is applied to a minimal thermal model of a satellite with ten isothermal parts (nodes), and the method is compared with direct numerical integration of the nonlinear equations. The computational complexity of this method is briefly studied for general thermal models of orbiting spacecraft, and it is concluded that it is certainly useful for reduced models and conceptual design but it can also be more efficient than the direct integration of the equations for large models. The results of the Fourier series computations for the ten-node satellite model show that the periodic solution at the second perturbative order is sufficiently accurate. A, C c, e a F(t) Fa(t) F,(t) F a(t) F(m) Fi(m) p* G(t)

show abstract

“…Other examples of detailed computational approaches include studies of ICESAT [11] and JASON-1 [12]. Simplified analytical models for transient heating scenarios are also presented in [13].…”

mentioning

confidence: 99%

Modeling and Validation of Thermal Radiation Acceleration on Interplanetary Spacecraft

Shoemaker

Ha²,

Morley

2012

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

Precise modeling of nonconservative forces is becoming increasingly important for deep-space and interplanetary missions, especially those with strict targeting requirements. Apparent errors in the solar radiation pressure model are often corrected with estimated scale factors in the orbit determination process. For example, several European Space Agency deep-space spacecraft have estimated solar radiation pressure scale factors between 1.05 and 1.15. This work shows that including separate thermal acceleration models can account for many of these apparent errors in the solar radiation pressure modeling. Using the Rosetta spacecraft as an example, a steady-state thermal model that is applicable to the cruise phases of interplanetary missions is described. The surface temperatures on the spacecraft body are solved in closed form, whereas those on the solar panel front and rear surfaces are solved with an iterative numerical procedure. The thermal model is validated by comparing the predicted thermal radiation acceleration with the remaining unmodeled acceleration extracted from the operational orbit estimates. The solar array temperatures from this model also agree with finite element method results and thermistor telemetry to within several degrees.

show abstract

Overview of Satellite Thermal Analytical Model

Cited by 58 publications

References 1 publication

Projection-Based Reduced-Order Modeling for Spacecraft Thermal Analysis

Projection-Based Reduced-Order Modeling for Spacecraft Thermal Analysis

Linear Approach to the Orbiting Spacecraft Thermal Problem

Modeling and Validation of Thermal Radiation Acceleration on Interplanetary Spacecraft

Contact Info

Product

Resources

About