Full text
|
PDF
- Requires a PDF viewer, such as GSview, Xpdf or Adobe Acrobat Reader
Download (3MB) | Preview |
Fernández-Rico, Germán and Pérez-Grande, María Isabel and Sanz Andres, Angel Pedro and Torralbo, Ignacio and Woch, Joachim (2016). Quasi-autonomous thermal model reduction for steady-state problems in space systems. "Applied Thermal Engineering", v. 105 ; pp. 456-466. ISSN 1359-4311. https://doi.org/10.1016/j.applthermaleng.2016.03.017.
Title: | Quasi-autonomous thermal model reduction for steady-state problems in space systems |
---|---|
Author/s: |
|
Item Type: | Article |
Título de Revista/Publicación: | Applied Thermal Engineering |
Date: | July 2016 |
ISSN: | 1359-4311 |
Volume: | 105 |
Subjects: | |
Faculty: | Instituto de Microgravedad Ignacio Da Riva (UPM) |
Department: | Aeronaves y Vehículos Espaciales |
UPM's Research Group: | Desarrollo y Ensayos Aeroespaciales DEA |
Creative Commons Licenses: | Recognition - No derivative works - Non commercial |
|
PDF
- Requires a PDF viewer, such as GSview, Xpdf or Adobe Acrobat Reader
Download (3MB) | Preview |
A matrix method is developed to reduce the number of elements of spacecraft thermal mathematical models based on the lumped parameter method. The aim of this method is to achieve a satisfactory thermal model reduction for steady-state problems, in an automatic way, while preserving the physical meaning of the system and the main characteristics of the model. The simplicity of the method, and the computational cost, are also taken into account. The reduction process is based on the manipulation of the conductive coupling matrix, which is treated as a sparse graph adjacency matrix. Then, a depthfirst search algorithm is used to find the strongly connected components, which define the condensed nodes. Finally, all the thermal entities are reduced, and the results from the condensed model are compared to those from the detailed one. The entire reduction process is tested on a real thermal model,showing a good performance. In the conclusions section the characteristics and limitations of this method are shown.
Type | Code | Acronym | Leader | Title |
---|---|---|---|---|
Government of Spain | AYA2012-39636-C06-04 | Unspecified | Unspecified | Diseño detallado, fabricación e integración de SO/PHI |
Government of Spain | ESP2013-47349-C6-4-R | Unspecified | Unspecified | Participación de IDR/UPM en Solar Orbiter: Fabricación, integración y verificación de PHI ; Contribución a ingeniería de sistemas de EPD |
Item ID: | 47150 |
---|---|
DC Identifier: | https://oa.upm.es/47150/ |
OAI Identifier: | oai:oa.upm.es:47150 |
DOI: | 10.1016/j.applthermaleng.2016.03.017 |
Official URL: | http://www.sciencedirect.com/science/article/pii/S1359431116303088 |
Deposited by: | Biblioteca ETSI Aeronauticos |
Deposited on: | 18 Jul 2017 11:04 |
Last Modified: | 31 Jul 2017 22:30 |