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.

Modeling and Analysis of a MEMS-Based Thermal Emissivity Variable Thermal Control Device

2013 ◽  
Vol 401-403 ◽  
pp. 1686-1690
Author(s):  
Da Hai Ren ◽  
Jing Feng Tian
Keyword(s):  
Control System ◽  
Theoretical Analysis ◽  
Thermal Control ◽  
Control Device ◽  
Modeling And Analysis ◽  
Thermal Emissivity ◽  
Thermal Control System ◽  
Electrostatic Torque ◽  
Control Devices ◽  
The Relationship

The study was made on a MEMS-based thermal emissivity variable micro-thermal control device to meet the requirements of the thermal control system of the spacecraft. An emissivity adjustment model for louvers was established. Main parameters that influence the equivalent emissivity of the louver were also investigated. Characteristics such as the electrostatic torque driven by parallel electrodes were modeled and analyzed. As a result, curves of the relationship between angles driven by parallel electrodes and electrostatic torques were obtained. Based on theoretical analysis, the adjustment range of the thermal emissivity was obtained for torsional micro-thermal control devices. The results showed that the properties meet the requirements for the control of space thermal emissivity.

PROCEDURE AND TOOLS FOR DEVELOPING THERMAL CONTROL SYSTEM FOR SCIENTIFIC SPACECRAFT EQUIPMENT

2013 ◽  
Vol 4 (3) ◽  
pp. 169-180
Author(s):  
S. A. Hryshyn ◽  
A. G. Batischev ◽  
S. V. Koldashov ◽  
Aliaksei L. Petsiuk ◽  
V. A. Seliantev ◽  
...  
Keyword(s):  
Control System ◽  
Thermal Control ◽  
Thermal Control System

DETERMINING THERMAL RESISTANCE IN THE MODEL OF THE LIQUID CIRCUIT OF SPACECRAFT THERMAL CONTROL SYSTEM

2019 ◽  
Vol 20 (3) ◽  
pp. 366-374
Author(s):  
Yu. N. Shevchenko ◽  
◽  
A. A. Kishkin ◽  
F. V. Tanasiyenko ◽  
O. V. Shilkin ◽  
...  
Keyword(s):  
Control System ◽  
Thermal Resistance ◽  
Thermal Control ◽  
Thermal Control System ◽  
Spacecraft Thermal Control

Design, Simulation and Test of Thermal Control System of Centrifuge for Space Utilization

2020 ◽  
Vol 32 (4) ◽  
pp. 761-772
Author(s):  
Yu Zhang ◽  
Shikui Dong ◽  
Ke Wang ◽  
Yanlin Zhou ◽  
Qiang Sheng ◽  
...  
Keyword(s):  
Control System ◽  
Thermal Control ◽  
Space Utilization ◽  
Thermal Control System
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