Hardware-in-loop-simulator for InnoSAT attitude control system
After launching, the initial condition of satellite is unknown and tends to be in a tumbling state. At this moment, the satellite needs to reduce the tumbling rate so that the satellite can enter a stable and unruffled state. The satellite also must maintain a certain attitude while orbiting in orde...
| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
| Published: |
Insight Society
2016
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| Subjects: | |
| Online Access: | View Fulltext in Publisher View in Scopus |
| Summary: | After launching, the initial condition of satellite is unknown and tends to be in a tumbling state. At this moment, the satellite needs to reduce the tumbling rate so that the satellite can enter a stable and unruffled state. The satellite also must maintain a certain attitude while orbiting in order to allow precise pointing of the antenna toward the earth. In this study, a hardware-in-loopsimulator was devised for the purpose of improving the design and verifying attitude control concepts for Innovative Satellite (InnoSAT) system. A new software architecture and algorithm was developed based on the controller, InnoSAT plant, actuator and sensor. Firstly, the controller, actuator and sensor was modelled in the MATLAB program together with InnoSAT plant. The actuator and sensor were assumed to be ideal. However, some properties of the actuator and sensor were simulated in the software simulator. If the software simulation performed satisfactorily, the control algorithm will be embedded into Rabbit Micro Controller (RCM4100) using Dynamic C language. This is the part where the hardware simulation is developed which is creating hardware-inloop- simulation technique for verification of InnoSAT Attitude Control System (ACS) performance. The satellite simulator was tested using simulated data in order to observe the performances of the controller in real time simulation. The results show that the InnoSAT ACS simulator can produce as good result as a MATLAB simulation for the InnoSAT plants. From the results, it is adequate to verify that the developed protocol working satisfyingly and seems to be possible to be implemented on the actual flight. |
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| ISBN: | 20885334 (ISSN) |
| ISSN: | 20885334 (ISSN) |
| DOI: | 10.18517/ijaseit.6.5.985 |