Numerical study of active cooling techniques of a nano satellite using CFD for performance enhancement

Vignesh Chandrasekaran, Mollik Nayyar, Srikanth Raviprasad, Yash Vardhan Gupta

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

All nano satellites experience a transient thermal environment in space. The main challenge in a nano satellite is the design of the subsystems within dimensional and weight constrains with no compromise on its performance due to external temperature variations. There are various components like printed circuit boards (PCBs), global positioning system (GPS) receiver, integrated circuits, batteries, magnetorquer which have a very specific temperature range of working, outside which their functional capabilities are not achieved. Due to the varying heat loads due to the sun earth and albedo, the heat experienced by the satellite has to be modelled for obtaining the temperatures attained by the various components on board. The most common passive temperature control systems used are the multi-layer insulation and paint, which have been in use for a very long time in nano satellites. However for a payload that requires critical temperature conditions to be maintained, it would be very difficult to control using passive methods. In this paper, an active thermal control method using a regenerative turbine pump is suggested. The pump circulates fluid through the designed heat path, where maximum cooling has to be achieved. The major challenges are in the selection of a fluid based on fluid properties like viscosity, boiling and freezing point. The rate of heat transfer is based upon the heat transfer coefficient and the operating conditions of the pump. For the first time, this will be implemented on a nano satellite level. The geometric modelling is done on CATIA V5 R19, thermal loads are modelled on Transient Thermal Analysis standalone system of ANSYS 14.0 Workbench and the fluid analyses are performed on ANSYS FLUENT. The results are extracted for post processing and optimization. This will revolutionize the idea of thermal control on nano satellites and break the trend of using passive thermal control systems providing flexibility for the thermal designers to innovate under the system constraints.

Original languageEnglish
Title of host publication64th International Astronautical Congress 2013, IAC 2013
PublisherInternational Astronautical Federation, IAF
Pages6119-6126
Number of pages8
Volume8
ISBN (Print)9781629939094
Publication statusPublished - 01-01-2013
Externally publishedYes
Event64th International Astronautical Congress 2013, IAC 2013 - Beijing, China
Duration: 23-09-201327-09-2013

Conference

Conference64th International Astronautical Congress 2013, IAC 2013
CountryChina
CityBeijing
Period23-09-1327-09-13

Fingerprint

charge flow devices
Computational fluid dynamics
Satellites
Cooling
cooling
augmentation
pump
fluid
fluids
Fluids
heat
temperature
heat transfer
Thermal load
control system
multilayer insulation
turbine pumps
pumps
thermal environments
Pumps

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Aerospace Engineering
  • Astronomy and Astrophysics

Cite this

Chandrasekaran, V., Nayyar, M., Raviprasad, S., & Gupta, Y. V. (2013). Numerical study of active cooling techniques of a nano satellite using CFD for performance enhancement. In 64th International Astronautical Congress 2013, IAC 2013 (Vol. 8, pp. 6119-6126). International Astronautical Federation, IAF.
Chandrasekaran, Vignesh ; Nayyar, Mollik ; Raviprasad, Srikanth ; Gupta, Yash Vardhan. / Numerical study of active cooling techniques of a nano satellite using CFD for performance enhancement. 64th International Astronautical Congress 2013, IAC 2013. Vol. 8 International Astronautical Federation, IAF, 2013. pp. 6119-6126
@inproceedings{e35da85c631741b58bacf230883feefe,
title = "Numerical study of active cooling techniques of a nano satellite using CFD for performance enhancement",
abstract = "All nano satellites experience a transient thermal environment in space. The main challenge in a nano satellite is the design of the subsystems within dimensional and weight constrains with no compromise on its performance due to external temperature variations. There are various components like printed circuit boards (PCBs), global positioning system (GPS) receiver, integrated circuits, batteries, magnetorquer which have a very specific temperature range of working, outside which their functional capabilities are not achieved. Due to the varying heat loads due to the sun earth and albedo, the heat experienced by the satellite has to be modelled for obtaining the temperatures attained by the various components on board. The most common passive temperature control systems used are the multi-layer insulation and paint, which have been in use for a very long time in nano satellites. However for a payload that requires critical temperature conditions to be maintained, it would be very difficult to control using passive methods. In this paper, an active thermal control method using a regenerative turbine pump is suggested. The pump circulates fluid through the designed heat path, where maximum cooling has to be achieved. The major challenges are in the selection of a fluid based on fluid properties like viscosity, boiling and freezing point. The rate of heat transfer is based upon the heat transfer coefficient and the operating conditions of the pump. For the first time, this will be implemented on a nano satellite level. The geometric modelling is done on CATIA V5 R19, thermal loads are modelled on Transient Thermal Analysis standalone system of ANSYS 14.0 Workbench and the fluid analyses are performed on ANSYS FLUENT. The results are extracted for post processing and optimization. This will revolutionize the idea of thermal control on nano satellites and break the trend of using passive thermal control systems providing flexibility for the thermal designers to innovate under the system constraints.",
author = "Vignesh Chandrasekaran and Mollik Nayyar and Srikanth Raviprasad and Gupta, {Yash Vardhan}",
year = "2013",
month = "1",
day = "1",
language = "English",
isbn = "9781629939094",
volume = "8",
pages = "6119--6126",
booktitle = "64th International Astronautical Congress 2013, IAC 2013",
publisher = "International Astronautical Federation, IAF",
address = "France",

}

Chandrasekaran, V, Nayyar, M, Raviprasad, S & Gupta, YV 2013, Numerical study of active cooling techniques of a nano satellite using CFD for performance enhancement. in 64th International Astronautical Congress 2013, IAC 2013. vol. 8, International Astronautical Federation, IAF, pp. 6119-6126, 64th International Astronautical Congress 2013, IAC 2013, Beijing, China, 23-09-13.

Numerical study of active cooling techniques of a nano satellite using CFD for performance enhancement. / Chandrasekaran, Vignesh; Nayyar, Mollik; Raviprasad, Srikanth; Gupta, Yash Vardhan.

64th International Astronautical Congress 2013, IAC 2013. Vol. 8 International Astronautical Federation, IAF, 2013. p. 6119-6126.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

TY - GEN

T1 - Numerical study of active cooling techniques of a nano satellite using CFD for performance enhancement

AU - Chandrasekaran, Vignesh

AU - Nayyar, Mollik

AU - Raviprasad, Srikanth

AU - Gupta, Yash Vardhan

PY - 2013/1/1

Y1 - 2013/1/1

N2 - All nano satellites experience a transient thermal environment in space. The main challenge in a nano satellite is the design of the subsystems within dimensional and weight constrains with no compromise on its performance due to external temperature variations. There are various components like printed circuit boards (PCBs), global positioning system (GPS) receiver, integrated circuits, batteries, magnetorquer which have a very specific temperature range of working, outside which their functional capabilities are not achieved. Due to the varying heat loads due to the sun earth and albedo, the heat experienced by the satellite has to be modelled for obtaining the temperatures attained by the various components on board. The most common passive temperature control systems used are the multi-layer insulation and paint, which have been in use for a very long time in nano satellites. However for a payload that requires critical temperature conditions to be maintained, it would be very difficult to control using passive methods. In this paper, an active thermal control method using a regenerative turbine pump is suggested. The pump circulates fluid through the designed heat path, where maximum cooling has to be achieved. The major challenges are in the selection of a fluid based on fluid properties like viscosity, boiling and freezing point. The rate of heat transfer is based upon the heat transfer coefficient and the operating conditions of the pump. For the first time, this will be implemented on a nano satellite level. The geometric modelling is done on CATIA V5 R19, thermal loads are modelled on Transient Thermal Analysis standalone system of ANSYS 14.0 Workbench and the fluid analyses are performed on ANSYS FLUENT. The results are extracted for post processing and optimization. This will revolutionize the idea of thermal control on nano satellites and break the trend of using passive thermal control systems providing flexibility for the thermal designers to innovate under the system constraints.

AB - All nano satellites experience a transient thermal environment in space. The main challenge in a nano satellite is the design of the subsystems within dimensional and weight constrains with no compromise on its performance due to external temperature variations. There are various components like printed circuit boards (PCBs), global positioning system (GPS) receiver, integrated circuits, batteries, magnetorquer which have a very specific temperature range of working, outside which their functional capabilities are not achieved. Due to the varying heat loads due to the sun earth and albedo, the heat experienced by the satellite has to be modelled for obtaining the temperatures attained by the various components on board. The most common passive temperature control systems used are the multi-layer insulation and paint, which have been in use for a very long time in nano satellites. However for a payload that requires critical temperature conditions to be maintained, it would be very difficult to control using passive methods. In this paper, an active thermal control method using a regenerative turbine pump is suggested. The pump circulates fluid through the designed heat path, where maximum cooling has to be achieved. The major challenges are in the selection of a fluid based on fluid properties like viscosity, boiling and freezing point. The rate of heat transfer is based upon the heat transfer coefficient and the operating conditions of the pump. For the first time, this will be implemented on a nano satellite level. The geometric modelling is done on CATIA V5 R19, thermal loads are modelled on Transient Thermal Analysis standalone system of ANSYS 14.0 Workbench and the fluid analyses are performed on ANSYS FLUENT. The results are extracted for post processing and optimization. This will revolutionize the idea of thermal control on nano satellites and break the trend of using passive thermal control systems providing flexibility for the thermal designers to innovate under the system constraints.

UR - http://www.scopus.com/inward/record.url?scp=84904654688&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84904654688&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:84904654688

SN - 9781629939094

VL - 8

SP - 6119

EP - 6126

BT - 64th International Astronautical Congress 2013, IAC 2013

PB - International Astronautical Federation, IAF

ER -

Chandrasekaran V, Nayyar M, Raviprasad S, Gupta YV. Numerical study of active cooling techniques of a nano satellite using CFD for performance enhancement. In 64th International Astronautical Congress 2013, IAC 2013. Vol. 8. International Astronautical Federation, IAF. 2013. p. 6119-6126