In this paper a fault tolerant control (FTC) system is designed and implemented on a constructed coarse sun sensor, called IUST-CSS. In this regard, fault study of the sensor is accomplished using fault tree analysis. Fault detection and diagnosis will be done after finding an optimal place to generate the residual signal in the closed loop system. Afterwards the simply realizable FTC algorithm is applied on the sun sensor in a developed spin satellite simulator. The simulator has the essential parts to provide not only the proper alignment of the sensor by the sun, but has also generated the spinning rate of the satellite. In order to evaluate the performance of the sensor and effectiveness of the FTC algorithm, outputs of the sensor are measured and transferred in to a remote PC. Experimental results are presented to demonstrate the feasibility of the system.
BlankeM.Izadi-ZamanabadiR.BøghS. A.LunauC. P., “Fault-Tolerant Control Systems - a Holistic View”, Control Engineering Practice, Vol. 5, No. 5, 693–702, 1997
2.
WimmerW. (1997), “Lessons to be Learned from European Science and Application Space Missions”, Control Engineering Practice5(2), pp 155–165
3.
ChangY. K.YunM. Y.LeeB. H., “A new modeling and validation of two-axis miniature fine sun sensor”, Sensors and Actuators A: Physical, Vol. 134, Issue 2, pp 357–365, 15 March 2007
4.
WertzJ. R., Spacecraft Attitude Determination and Control, WertzJ., Ed. Norwell, MA, Kluwer, 1995
5.
BolandiH.BadpaA.GhorbaniB., “Design of Gravity Gradient and Aerodynamic Passive Stabilization System for a LEO Satellite”, Journal of Automatic Control and Computer Science, ISI, No. 4, 2003
6.
BöhnkeT.EdoffM.StenmarkL., “Development of a MOEMS sun sensor for space applications”, Sensors and Actuators A: Physical, Vol. 130–131, pp 28–36, 14 August 2006.
7.
LeeJ.Di FilippoK.NgA.RibeC., “Modeling and Simulation of A Commercial Medium Sun Sensor”, Control and Automation, 2003. ICCA apos. 03. Proceedings. 4th International Conference, pp 728–732, 10–12 June 2003
8.
Trebi-OllennuA.HuntsbergerT., “Design and Analysis of a Sun Sensor for Planetary Rover Absolute Heading Detection”, IEEE Transactions on Robotics and Automation, Vol. 17, No. 6, December 2001
9.
FisherH. L.MusserK. L.SwsterM. D., ‘Coarse Attitude Determination From Earth Albedo Measurements’, IEEE Transactions on Aerospace and Electronic Systems, Vol. 29, No. 1, January 1993
10.
SidiM. J., Spacecraft Dynamics and Control, Cambridge University Press, 1997
PedersenM.HalesJ. H., “Linear Two-Axis Moems Sun Sensor and the need for Mems in Space”, DK-2800 Kgs. Lyngby, Denmark, 54th International Astronautical Congress
15.
KempR. F.SellenJ. M.Jr., “Solar wind simulation with the Pioneer spacecraft”, AIAA-1966-153 American Inst Of Aeronautics And Astronautics, Plasmadynamics Conference, Monterey, Calif., Mar 2–4, 1966, Paper 66–153. 24 P. 8 Refs.
16.
DahlH.., “ACE - A Canadian Small Science Satellite Mission”, 13th AIAA/USU Conference on Small Satellite
17.
BolandiH.SoleimanzadehM.GhorbaniVagheii B., “Design and construction of an analog sun sensor for attitude determination of spacecraft”, 14th Iranian Conference on EE (ICEE2006), May 2006
18.
BolandiH.SoleimanzadehM.GhorbaniVagheii B.“A Coarse Sun Sensor for Attitude Determination of Spacecraft”, The 6th Iranian Aerospace Society Conference-AERO2007, Feb. 2007
19.
BolandiH.SoleimanzadehM.GhorbaniVagheii B., “Derivation of Performance Model of a Constructed Analog Sun Sensor”, 15th Iranian Conference on EE (ICEE2007), May 2007
20.
PradoJ.BisiacchiG.. “Three-axis Air-Bearing Based Platform for Small Satellite Attitude Determination and Control Simulation”Journal of Applied Research and Technology, Vol. 3, pp 222–237, December 2005
21.
KimB.VelenisE.KriengsiriP.TsiotrasP., “A Spacecraft Simulator for Research and Education” in Proceedings of the AIAA/AAS Astrodynamics Specialists Conference, No. AAS 01–367, (Quebec City, Quebec, Canada), pp 897–914, July 30-August 2, 2001
22.
ThurberR., “Dynamic Ground Simulation of Attitude Control Systems” in Proceedings of the 35th AIAA Aerospace Sciences Meeting & Exhibit, No. AIAA 97-0010, (Reno, Nevada), January 6–9, 1997
23.
SpencerM. G.CherneskyV.BakerJ.RomanoM., “Bifocal Relay Mirror Experiments on the NPS Three Axis Spacecraft Simulator” in Proceedings of the AIAA Guidance, Navigation, and Control Conference and Exhibit, No. AIAA 02-5031, (Monterey, California), August 5–8, 2002
24.
XuY.JiangJ., “Optimal Sensor Location in Closed-Loop Control Systems for Fault Detection and Isolation”, Proceedings of the American Control Conference Chicago, Illinois June 2000
25.
“Fault Tree Handbook with Aerospace Applications”, prepared for NASA Office of Safety and Mission Assurance NASA Headquarters Washington, DC 20546, August, 2002
26.
Van BreukelenE.D.HamannR.J.OverboschE.G., “Qualitative fault tree analysis applied as a design tool in a low cost satellite design: Method and lessons learned”, System Integration, Design and Analysis of Space Systems, Delft University of Technology, The Netherlands, May 2006
27.
BolandiH.SoleimanzadehM.GhorbaniVagheii B.“Implementing a FTC method for IUST-CSS sun sensor in a spinning satellite” The 7th Iranian Aerospace Society Conference-AERO2008, Feb. 2008
28.
BolandiH.TeimuriH., “Determination of the best place in ADCS in order to Fault Detection”, 10th Annual Conference (International) on Mechanical Engineering, May 2002.
29.
XuY.JiangJ., “Optimal Sensor Location in Closed-Loop Control System for Fault Detection and Isolation”, Proceedings of the American Control Conference, Chicago, Illinois, June 2000.
