Attitude Determination System For Nano Satellite Using Extended Kalman Filter On ARM7TDMI Platform
Extended Kalman Filter (EKF) has been successfully utilized in satellites missions. However, in comparison to other attitude determination methods developed, it is one of the most computationally burdening algorithm and with the new development of using nano satellites which have limited electric...
محفوظ في:
| المؤلف الرئيسي: | |
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| التنسيق: | أطروحة |
| اللغة: | English |
| منشور في: |
2014
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| الموضوعات: | |
| الوصول للمادة أونلاين: | http://eprints.usm.my/28966/1/ATTITUDE_DETERMINATION_SYSTEM_FOR_NANO_SATELLITE_USING_EXTENDED_KALMAN_FILTER_ON_ARM7TDMI_PLATFORM.pdf |
| الوسوم: |
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| الملخص: | Extended Kalman Filter (EKF) has been successfully utilized in satellites missions.
However, in comparison to other attitude determination methods developed, it is one of
the most computationally burdening algorithm and with the new development of using
nano satellites which have limited electrical power, mass, space and usually budget, it
is essential to design an Attitude Determination System (ADS) which conforms to this
limitation. Therefore, in this thesis, as a computational improvement on the InnoSAT
project, the RCM3400 microcontroller of the ADS is replaced with the ARM7TDMI
based microprocessor to test its capability.
Penapisan Kalman Lanjutan (PKL) telah digunakan dengan jayanya di dalam misi
satelit. Akan tetapi, jika dibandingkan dengan kaedah penentuan kedudukan lain
yang telah dihasilkan, ia adalah salah satu daripada algoritma yang memiliki komputasi
yang paling berat dan dengan perkembangan terkini yang menggunakan satelit
nano yang mempunyai kuasa elektrik, berat, ruang dan biasanya peruntukan yang
terhad, adalah menjadi satu keutamaan untuk merekabentuk sebuah Sistem Penentuan
Kedudukan (SPK) yang dapat mematuhi kekangan ini. |
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