Orbit Determination via a Deeply- Coupled UKF/GNSS Filter
This paper is dedicated to determining the orbit of a satellite by using Unscented Kalman Filter (UKF), in which, a GNSS is used as the observation sensor. During this goal, firstly we have simulated the satellite orbit; considering oblations effect. Secondly, exploiting a nonlinear model of orbit d...
| الحاوية / القاعدة: | فصلنامه علوم و فناوری فضایی |
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| المؤلفون الرئيسيون: | , , |
| التنسيق: | مقال |
| اللغة: | الفارسية |
| منشور في: |
Aerospace Research Institute
2016-11-01
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| الموضوعات: | |
| الوصول للمادة أونلاين: | https://jsst.ias.ir/article_44472_82d57b3de3b310bdfd7b33d32dc189bf.pdf |
| الملخص: | This paper is dedicated to determining the orbit of a satellite by using Unscented Kalman Filter (UKF), in which, a GNSS is used as the observation sensor. During this goal, firstly we have simulated the satellite orbit; considering oblations effect. Secondly, exploiting a nonlinear model of orbit dynamics, preliminary orbit determination is prepared via UKF algorithm. The range between the satellites and space vehicle as the parameter of observation in the filter is obtained. Afterwards, the estimated preliminary output data is corrected and more precise position of the GNSS satellite is determined based on predicted observations errors. Consequently, the outcomes of the research exhibits the acceptable satellite orbit determination error range. |
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| تدمد: | 2008-4560 2423-4516 |