Spacecraft thermal control

Meseguer, José; Pérez-Grande, Isabel; Sanz-Andrés, Ángel

doi:10.1533/9780857096081

Cited by 119 publications

(89 citation statements)

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“…The reason why the contact thermal resistances change is that the contact heat conductivity will change, for the air will fill in little crevices of the contact interface so more heat could be conduct through the interface. Usually the value of contact thermal conductivity could be improved one or two order higher in air condition [1][2][3]. The convection changes obviously because there is no convection heat transfer in vacuum.…”

Section: Information and Structure Of The Electric Boxmentioning

confidence: 99%

A Discuss on a Thermal Conductive Panel of FPGA

Chen¹,

Li²,

Yin³

et al. 2017

dtetr

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Abstract. In this paper a mounted problem about a thermal conductive panel which is used for a FPGA chip being used on satellite and in vacuum environment is discussed. In order to decide whether the panel could be un-mounted when carrying electronic testing in air condition under high and low temperature environment, a simulation analysis is done and the different of convection for the air condition and the thermal contact resistance is considered. The analysis results showed that the temperature of FPGA un-mounting the thermal conductive panel is within the permitted temperature and the final testing have been done in which the box work well. Through the efficiency analysis the time cost and project cost are all saved.

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Section: Information and Structure Of The Electric Boxmentioning

confidence: 99%

A Discuss on a Thermal Conductive Panel of FPGA

Chen¹,

Li²,

Yin³

et al. 2017

dtetr

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“…We denote by L(y) to the lift force in a generic airfoil located at y ∈ [0, l]. This force per unit-length can be calculated following the classic aerdoynamic theory of slender lifting surfaces (Anderson, 2001;Meseguer & Sanz-Andrés, 2010) and can be expressed as…”

Section: Task 3: Static Aeroelasticitymentioning

confidence: 99%

A Teaching Experience: Aeroelasticity and the Finite Element Method

Lázaro

2015

Model. sci. educ. learn.

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The aeroelastic modelling of aircraft structures is a fundamental area for the students of Aerospace Engineering Degree. This subject has a strongly multidisciplinary character and involves other several subjects like mechanics, vibrations, aerodynamics, structural analysis. Consequently, the students find stimulating the challenge of merging their knowledge at different areas. In this paper, a teaching experience on the solution of the aeroelastic problem of a 3D-wing through six different computer tasks is presented. The main objective is to attempt a relatively complex problem using a simple version of the Finite Element Method with only four degrees of freedom. The students begin creating the shape functions of the discrete model and finish solving the flutter instability problem. La modelización aeroelástica de estructuras aeronáuticas es una materia fundamental en la formación de estudiantes de Grado de Ingeniería Aeroespacial. Esta materia tiene es multidisciplinar e involucra diferentes asignaturas vistas durante los estudios como mecánica, vibraciones, aerodinámica o estructuras. Por ello, los estudiantes encuentran estimulante el reto de fusionar sus conocimientos en diferentes areas en una sola asignatura. En este artículo se presenta una experiencia docente en la que se busca resolver el problema aeroelástico de un ala a través de 6 prácticas informáticas. El objetivo es poder abordar un problema tridimensional a priori relativamente complejo con una herramienta de gran utilidad en la mecánica computacional como es el método de los elementos finitos. Los estudiantes comienzan creando las funciones de forma para el modelo discreto y acaban resolviendo el problema de inestabilidad dinámica, el flameo

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“…A number of analytical and numerical methods have been developed such as the Glauert and Goldstein methods developed to study improper integrals that appear in this setting, [6][7][8][9][10][11], which are relevant in aerodynamics. In fact, aerodynamic entropy study focuses on the overall performance neglecting singularities that enjoy some symmetric entropic phenomena such as turbulence on wing or rotor blades and for this Cauchy principal values are commonly used [12][13][14]. Cauchy principal value contour integrals have recently arisen inspired by the real case definition, [15].…”

Section: Introductionmentioning

confidence: 99%

Cauchy Principal Value Contour Integral with Applications

Legua

Ruiz

2017

Entropy

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Cauchy principal value is a standard method applied in mathematical applications by which an improper, and possibly divergent, integral is measured in a balanced way around singularities or at infinity. On the other hand, entropy prediction of systems behavior from a thermodynamic perspective commonly involves contour integrals. With the aim of facilitating the calculus of such integrals in this entropic scenario, we revisit the generalization of Cauchy principal value to complex contour integral, formalize its definition and-by using residue theory techniques-provide an useful way to evaluate them.

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Spacecraft thermal control

Cited by 119 publications

References 0 publications

A Discuss on a Thermal Conductive Panel of FPGA

A Discuss on a Thermal Conductive Panel of FPGA

A Teaching Experience: Aeroelasticity and the Finite Element Method

Cauchy Principal Value Contour Integral with Applications

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