| dc.contributor.author | Renuganth, Varatharajoo | |
| dc.contributor.author | Aznijar, Ahmad Yazid | |
| dc.contributor.author | Mohd Ramly, Ajir | |
| dc.date.accessioned | 2011-08-10T09:17:31Z | |
| dc.date.available | 2011-08-10T09:17:31Z | |
| dc.date.issued | 2004-03 | |
| dc.identifier.citation | The Journal of the Institution of Engineers, Malaysia, vol. 65(1/2), 2004, pages 13-19 | en_US |
| dc.identifier.issn | 0126-513X | |
| dc.identifier.uri | http://myiem.org.my/content/iem_journal_2004-175.aspx | |
| dc.identifier.uri | http://dspace.unimap.edu.my/123456789/13425 | |
| dc.description | Link to publisher's homepage at http://www.myiem.org.my/ | en_US |
| dc.description.abstract | The synergistic system design could be an attractive approach for future spacecraft to cope with their demands. The idea of
combining the Attitude Control System and the conventional Electrical Power System is presented here. In this article, the Combined
Energy and Attitude Control System (CEACS), a double counter rotating flywheel assembly in the pitch axis, is investigated for small
satellites. The performance of CEACS is demonstrated for a selected configuration and mission. Another idea of incorporating the
Attitude Control System into the Thermal Control System is also investigated. The Combined Attitude and Thermal Control System
(CATCS)* consisting of a “fluid wheel” and permanent magnets, couples an existing onboard temperature gradient with the magnetohydrodynamic
(MHD) effects for its operation. The performance of CATCS is demonstrated for a reference configuration and mission.
The CEACS and CATCS are potential synergistic systems for the future spacecraft. | en_US |
| dc.language.iso | en | en_US |
| dc.publisher | The Institution of Engineers, Malaysia | en_US |
| dc.subject | Flywheel | en_US |
| dc.subject | Fluid wheel | en_US |
| dc.subject | Spacecraft attitude control | en_US |
| dc.title | Synergistic systems for spacecraft attitude control | en_US |
| dc.type | Article | en_US |
