GMES Sentinel 1: Thermal Design and Verification Approach of the Thermal Control Subsystem

2011 ◽  
Author(s):  
Daniela Selci ◽  
C. Bruno ◽  
Aniceto Panetti ◽  
M. L'Abbate ◽  
Silvio Dolce
Keyword(s):  
Thermal Control ◽  
Thermal Design ◽  
Control Subsystem

Software Development for Satellite Thermal Design

2013 ◽  
Vol 390 ◽  
pp. 703-707
Author(s):  
Abolfazl Shirazi ◽  
Mehran Mirshams
Keyword(s):  
Thermal Analysis ◽  
Temperature Gradient ◽  
Software Development ◽  
Research Laboratory ◽  
Thermal Control ◽  
Thermal Design ◽  
Temperature Gradients ◽  
Space Research ◽  
Accurate Analysis ◽  
Control Subsystem

Accurate thermal modeling for each part in the satellite is needed for achieving temperature gradients. The result of such a modeling will be the temperature gradients of each element of the satellite as a function of time. The aim of this paper is to present a new software which has been developed recently by the author at Space Research Laboratory for thermal analyzing of the satellites that is used to characterize the gradients of subsystems temperature as a function of time in space orbit. The software accomplishes accurate analysis of internal and external thermal loads of each part of the satellite and shows temperature gradients of each element. The purpose of designing this software is to create a useful application for thermal analysis of satellites, which is a helpful manner for testing satellite thermal subsystem. The most important usages of this software are designing thermal control subsystem, choosing proper equipment for thermal control subsystem and finding optimal configuration of satellite for having an ideal temperature gradient. The outputs of this software are validated by comparing them to a different thermal analyzing application.

Regenerable Non-Venting Thermal Control Subsystem for Extravehicular Activity, 1986

1986 ◽  
Author(s):  
George J. Roebelen ◽  
Stephen A. Bayes ◽  
B. Mike Lawson
Keyword(s):  
Thermal Control ◽  
Extravehicular Activity ◽  
Control Subsystem

Structure Design for Heat Sink Based on Thermal Analysis

2011 ◽  
Vol 80-81 ◽  
pp. 767-773
Author(s):  
Hai Gang Sun ◽  
Yong Zhou
Keyword(s):  
Thermal Analysis ◽  
Thermal Performance ◽  
Heat Sink ◽  
Cfd Simulation ◽  
Thermal Control ◽  
Structure Design ◽  
Thermal Design ◽  
Structure Parameters ◽  
Igbt Module ◽  
Key Factor

Thermal design and the working temperature control have been a key factor in the design of electronic devices and system. In this paper, a sort of heat sink collocated with high-power IGBT module, which is commonly used in car-carrying motor control system, is designed based on thermal analysis by means of CFD simulation and computer-aided analyzing, also the influence relations of structure parameters with thermal performance are studied. With thermal control as the overall design objective, structure parameters of heat sink are determined according to the obtained relations. Further, thermal performance of the designed heat sink is simulated and analyzed in CFD software to examine the validity of the design result. In this way, a method of thermal analyzing and structure parameter design for heat sink, which is proved as an efficacious approach, is introduced and can be used to thermal design and analysis for similar products.

An Insight into the Features of the OAO-C Thermal Design

1973 ◽  
Vol 95 (4) ◽  
pp. 1039-1047 ◽  
Author(s):  
H. Fine ◽  
J. Quadrini ◽  
S. Ollendorf
Keyword(s):  
Thermal Control ◽  
Astronomical Observatory ◽  
Thermal Design ◽  
Test Bed ◽  
Large Space ◽  
Flight Data ◽  
The Earth ◽  
Ground Test ◽  
Earth Observation Satellite ◽  
Insight Into

The Orbiting Astronomical Observatory (OAO)-C was successfully launched into 400-nautical mile circular orbit on August 21, 1972. For this spacecraft, a unique sensitivity approach to the thermal design was developed which resulted in a predictal design—the merits of which should be considered for application on future spacecra. The OAO-C is also serving as a test bed for the evaluation of thermal control hardware. To provide flight data for space program applications, experiments for a new coating and four different heat pipe designs are on this spacecraft. The data derived from OAO-C will be extremely valuable for such future programs as the Large Space Telescope (LST) and the Earth Observation Satellite (EOS). This paper will describe the detailed of the sensitivity design approach and thermal control hardware. For all aspects discussed, a comparison of pertinent analysis, ground test data, and flight data [1] will be given.

Specific Heat Capacity Measurement of Al / SiCp Composites by Differential Scanning Calorimeter

2011 ◽  
Vol 264-265 ◽  
pp. 669-674 ◽  
Author(s):  
B. Karthikeyan ◽  
S. Ramanathan ◽  
V. Ramakrishnan
Keyword(s):  
Specific Heat ◽  
Volume Fraction ◽  
Thermal Control ◽  
Stir Casting ◽  
Thermal Design ◽  
Capacity Measurement ◽  
Scanning Calorimetry ◽  
Heat Measurement ◽  
Casting Technique ◽  
Materials Used

Various materials are used to achieve a good “Thermal Control System” (TCS) of spacecraft. The performance of the TCS totally depends upon the thermal behaviour of the materials used in the elements of TCS. The measurements of the thermal properties of materials are fundamental for better understanding of the thermal design. Differential Scanning Calorimetry (DSC) is the most widely used thermal technique for obtaining a wealth of information about a material, especially for the specific heat measurement of a material. Stir casting technique was used to fabricate the 7075 aluminum alloy and 7075 Al / SiCp composites. The heat flow response is recorded as a function of actual sample temperature range from -1000 C to 4000 C. Specific heat characteristics of 7075 Al reinforced with different volume fraction of silicon carbide composites fabricated by stir casting method was analyzed.

Specific Heat Measurements of Ti6Al4V/Nano SiCp Composite

2017 ◽  
Vol 14 (1) ◽  
pp. 742-746
Author(s):  
S Krishnamohan ◽  
S Ramanathan ◽  
V Ramakrishnan
Keyword(s):  
Heat Capacity ◽  
Weight Ratio ◽  
Thermal Control ◽  
Ti6al4v Alloy ◽  
Thermal Design ◽  
Thermal Method ◽  
Scanning Calorimetry ◽  
Low Weight ◽  
Wide Range ◽  
Materials Used

The elevated strength, low weight ratio and excellent corrosion resistance intrinsic to titanium and its alloys has led to a wide range of successful applications which ensures high levels of unswerving performance in aerospace. The performance of the Thermal Control System extremely depends on the thermal behavior of the materials used in its elements. The measurements of the thermal properties of materials are necessary for better understanding of the thermal design. Differential scanning calorimetry (DSC) is the most extensively used thermal method for finding wealth of information about a material. The heat capacity (Cp) of a material was established quantitatively using DSC. The measurement was made by heating a very small quantity of the Ti6Al4V alloy and Ti6Al4V/Nano SiCp composites. Mechanical alloying (MA) and Powder metallurgy (P/M) techniques were used to fabricate the Ti6Al4V alloy and Ti6Al4V/ nano SiCp composites. The heat flow reaction was recorded as a function of definite sample temperature range from −100 °C to 375 °C. The measurements of the heat capacity of each sample in three runs were recorded by DSC. The heat capacity (Cp) of specimens is reported in this study.

The Microstructure and Thermochromic Properties of La1-XSrXMnO3 Smart Materials

2013 ◽  
Vol 690-693 ◽  
pp. 648-653 ◽  
Author(s):  
Min Xu ◽  
Zhao Hui Fu ◽  
Lin Li ◽  
Jie Bing Wang ◽  
Chun Hua Wu ◽  
...  
Keyword(s):  
Smart Materials ◽  
Thermal Control ◽  
Solid State Reaction Method ◽  
Thermal Design ◽  
Radiative Properties ◽  
X Ray Diffraction ◽  
Conventional Solid State Reaction ◽  
Thermal Radiative Properties ◽  
Potential Applications ◽  
Thermochromic Properties

The La1-xSrxMnO3 materials have potential applications in thermal control systems of microsatellites. The microstructure of La1-xSrxMnO3 materials is very sensitive to the compound of Sr incorporated into it. In this paper, preparation process of La1-xSrxMnO3 compounds was explored. Ceramic sintering process combined with a conventional solid state reaction method was used to prepare various components of La1-xSrxMnO3。 Annealing temperature, time and doped ratio were controlled in the experiment. X-ray diffraction and Raman spectroscopy were used to analyze phase structure and crystalline. Thermal radiative properties were measured on a Calorimetric Emissometer at 175K～375K. These investigations reveal that microstructure of La1-xSrxMnO3 compounds are affected by Sr2+doping level(x).Thermal emissivity of La0.825Sr0.175MnO3 materials vary widely from 0.68 to 0.37, which can meet requirement of future space thermal design.

Thermal Control Subsystem for Free Flying Satellites

1982 ◽  
Author(s):  
Bob J. Jackson ◽  
David Rogers
Keyword(s):  
Thermal Control ◽  
Control Subsystem
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