Design and Analysis for Thermal Control System of Nanosatellite

2010 ◽  
Author(s):  
Murat Bulut ◽  
Adem Kahriman ◽  
Nedim Sozbir
Keyword(s):  
Thermal Analysis ◽  
Thermal Model ◽  
Thermal Control ◽  
Temperature Data ◽  
Thermal Design ◽  
Analysis Tool ◽  
Control Analysis ◽  
Preliminary Design ◽  
Thermal Control System ◽  
Early Phases

It is desirable to be able to turn-around thermal analysis results in a couple of minutes early phases of a satellite thermal design. Therefore, ThermXL-spreadsheet-based Thermal Analysis Tool is one of the very flexible and easy-to-use tool that is suited to preliminary design of a nanosatellite. This paper focuses on the thermal design and the results of an initial analysis of the nanosatellite by using ThermXL. The goal of this study is to take suitable measures to ensure all the components will operate in their safe range of temperatures and also a proper heat rejection. The nanosatellite such as Cube Satellite (CubeSat) is a miniaturized satellite that has dimensions of 10cm × 10cm × 10cm and weights of 1kg. The thermal model of CubeSat was modelled and the thermal analysis was performed. The thermal control analysis on this CubeSat with passive thermal control has been conducted by the ThermXL program that provided by ITP Engines. Temperature distribution of solutions was computed with ThermXL. Temperature data met the need of the mission. The results of the temperatures show that the thermal design of nanosatellite is feasible.

scholarly journals Quasi-All-Passive Thermal Control System Design and On-Orbit Validation of Luojia 1-01 Satellite

Sensors ◽  
2019 ◽  
Vol 19 (4) ◽  
pp. 827 ◽  
Author(s):  
Lin Yang ◽  
Qiang Li ◽  
Lin Kong ◽  
Song Gu ◽  
Lei Zhang
Keyword(s):  
Thermal Analysis ◽  
Control System ◽  
Temperature Fluctuation ◽  
Thermal Control ◽  
Temperature Data ◽  
Thermal Design ◽  
Analysis Model ◽  
Telemetry Data ◽  
Thermal Control System ◽  
Fluctuation Range

In order to resolve the large fluctuations in temperature range problem of Luojia 1-01 satellite caused by low heat inertia and poor thermal conductivity of structure, a quasi-all-passive thermal control system (TCS) design is presented under the conditions of limited resources including mass and power consumption. The effectiveness of the TCS design is verified by both ground thermal balanced test and related telemetry data of on-orbit performance. Firstly, according to the structural features and working modes of the satellite, isothermal design was implemented and the effectiveness was verified by thermal analysis using finite element method. Secondly, based on the results of the thermal analysis, thermal design was optimized and verified by the thermal balanced test. Finally, the thermal design was proved to be effective by temperature data acquired from telemetry data of on-orbit performance, and the thermal analysis model was improved and updated based on the results of thermal balanced test and temperature data of on-orbit performance. The on-orbit data indicates that temperature of optical camera stables at about 12 °C, temperature of battery stables at 19 °C, temperature of instruments inside and outside the satellite cabin is ranging from 10 °C to 25 °C. Temperature fluctuation range of optical camera is less than 2 °C when it is not imaging. Temperature fluctuation range of instruments not facing the sun is less than 4 °C. The data suggests that the temperature level of the satellite meets general design requirements, and the quasi-all-passive TCS design of the satellite is practicable.

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.

scholarly journals Simulation of the thermal control system of nanosatellite using the loop heat pipes under the orbital flight conditions

2021 ◽  
Vol 22 (1) ◽  
pp. 23-35
Author(s):  
Yu Wang ◽  
Oleg V. Denisov ◽  
Liliana V. Denisova
Keyword(s):  
Control System ◽  
Thermal Regime ◽  
Thermal Power ◽  
Heat Removal ◽  
Heat Pipes ◽  
Thermal Control ◽  
Thermal Design ◽  
Loop Heat Pipes ◽  
Thermal Control System ◽  
Design Power

One of the key problems in the development of nanosatellites is to provide a given temperature range for the operation of the on-board computer. The constantly increasing information load leads to the need to use more advanced processors with high thermal design power (TDP). The indicated thermal regime of processors can be achieved using remote heat removal systems - miniature loop heat pipes. Using a model of nanosatellite as an example, a thermal control system with miniature loop heat pipes is designed. The simulation was carried out in the Siemens NX program in the elliptical and geostationary orbits of the Earth. The cooling schemes of the processor with a thermal power of 15 W using one and two loop heat pipes are considered. Calculations showed that the use of loop heat pipes can reduce the processor temperature to acceptable values. The anisotropy of the thermal conductivity coefficient in the reinforcement plane of the composite material of the nanosatellite case can have a significant effect on the temperature of the processor. This opens up prospects for the use of anisotropic composite materials to ensure the thermal regime of the nanosatellite.

Investigation Regarding Transient Compact Thermal Model for Microprocessor Packages

2019 ◽  
Author(s):  
Koji Nishi
Keyword(s):  
Power Efficiency ◽  
Thermal Model ◽  
Three Dimensional ◽  
Transient State ◽  
Thermal Control ◽  
Computing System ◽  
Thermal Simulation ◽  
Thermal Design ◽  
Time Step ◽  
Transient Thermal

Abstract In recent years, not only static thermal design but also realtime thermal control become important for power efficiency on computing systems. Three-dimensional thermal simulation is widely used to design computing system, however, it takes too long time for intelligent power and thermal management validation because it requires transient thermal simulation with very short time step. To enable rapid simulation environment, compact thermal model which can be employed with both three-dimensional transient thermal simulation and transient thermal network is required. Therefore, this research aims to establish transient state compact thermal model for microprocessor package. This paper briefly introduces steady state compact thermal model for microprocessor, which is proposed as previous work, then, points out key point to extend the model to transient state model. Transient thermal spreading resistance is emulated and the effect is checked by comparing with three-dimensional simulation.

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.

AGILE Satellite Thermal Control System Design: Thermal Model Uncertainty Reduction

2007 ◽  
Author(s):  
Marco Molina ◽  
Matteo Giacomazzo ◽  
Paolo Sabatini ◽  
Christian Vettore ◽  
Giovanni Annoni ◽  
...  
Keyword(s):  
Control System ◽  
System Design ◽  
Model Uncertainty ◽  
Thermal Model ◽  
Thermal Control ◽  
Uncertainty Reduction ◽  
Control System Design ◽  
Thermal Control System ◽  
Agile Satellite

scholarly journals A university small satellite thermal control modeling and analysis in the post-mission phase

2021 ◽  
Vol 49 (4) ◽  
pp. 1014-1024
Author(s):  
Ahmed Elhefnawy ◽  
Ali Elmaihy ◽  
Ahmed Elweteedy
Keyword(s):  
Control System ◽  
Final Analysis ◽  
Thermal Control ◽  
Control Analysis ◽  
Modeling And Analysis ◽  
Component Distribution ◽  
Thermal Requirements ◽  
Thermal Control System ◽  
Internal Component ◽  
Control Modeling

This work includes the thermal control analysis of a small spacecraft in the post-mission phase. The satellite internal component distribution has been modified to fulfill all thermal requirements when using a passive thermal control system. In the post-mission phase, the satellite will be used by the radio Amateur Satellite Corporation (AMSAT) community as a transponder, fully using the AMSAT payload that will maintain active and shall last at least 2 years. Thermal Desktop software is introduced for the mentioned spacecraft. The final analysis predictions show that the passive thermal control system maintains all satellite element's temperatures within their temperature limits. The temperature variation of +X solar panel is 75 °C which is less than experienced by +Z and -Z panels, which are 100 °C. The temperature change on equipment agrees with their panels. Compared with a specialized thermal analysis, software package (ESATAN-TMSs) verified the integrity of the results.

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