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Ukf adaptation and filter integration for attitude determination and control of nanosatellites with magnetic sensors and actuators

Başlık çevirisi mevcut değil.

  1. Tez No: 508748
  2. Yazar: HALİL ERSİN SÖKEN
  3. Danışmanlar: Prof. SHINICHIRO SAKAI
  4. Tez Türü: Doktora
  5. Konular: Astronomi ve Uzay Bilimleri, Astronomy and Space Sciences
  6. Anahtar Kelimeler: Belirtilmemiş.
  7. Yıl: 2013
  8. Dil: İngilizce
  9. Üniversite: Graduate University for Advanced Studies (SOKENDAI)
  10. Enstitü: Yurtdışı Enstitü
  11. Ana Bilim Dalı: Belirtilmemiş.
  12. Bilim Dalı: Belirtilmemiş.
  13. Sayfa Sayısı: 130

Özet

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Özet (Çeviri)

The main aim of this study is to design an accurate attitude determination and control system for the nanosatellites with magnetic sensors and actuators. This aim is achieved by discussing different estimation algorithms, integrating them and finally proposing an overall attitude determination scheme. The given methods might be regarded both as separate solutions for different practical issues or a part of a whole attitude determination and control system for a nanosatellite. As a consequence of the progress in the miniaturization and the increase in the capability of the electronic devices, performing space missions with smaller satellites has become possible. The number of researches on such satellites is increasing day by day because of their advantages such as low investment and operational costs, enabling COTS (commercial of the shell) technology in space and short system development periods. Despite these facts discussions on small satellite attitude control is far from being concluded. Conceptual design limitations like the size and weight are the main reasons for the complexity of the problem yet such limitations are also what make the problem more interesting. The primary target of the researchers working on this issue is to design an attitude determination and control system, which can provide the same accuracy with the system for larger competitors, but remain within the design limitations. Magnetic sensors and actuators are popular attitude determination and control hardware for the nanosatellites since they are lighter, smaller and more economical compared to the others. On the other hand, they are regarded as coarse sensors and actuators and the accuracy that they can provide is limited because of the practical issues such as magnetic bias, residual magnetic moment and inherent complexity of the magnetic control. This study proposes new methods to overcome these limitations. In this context some of the subissues that are addressed are the on-orbit real time calibration of the magnetometers, adaptive tuning of the Kalman filter algorithm to increase the attitude estimation performance, robust estimation algorithm against sensor faults and estimation of the residual magnetic moments. The main contribution of this study is to examine several basic practical problems met for the attitude determination and control of a nanosatellite with magnetic sensors and actuators, and give a whole attitude determination algorithm, which is composed of adaptive filters, for solving these problems and increasing the attitude determination and control system performance. An approach based on the adaptation of the Unscented Kalman Filter, the estimation algorithm used as a part of the attitude determination procedure, is followed. The practical problems are solved stage by stage by using new techniques for the filter adaptation and then these filters are integrated in order to propose an overall attitude determination method. At the end a novel attitude determination scheme for nanosatellites with magnetic sensing and actuation is presented. Moreover the different estimation algorithms given in this paper have significance in terms of the estimation theory. The Robust Unscented Kalman Filter against sensor malfunctions and the Kalman filter adaptation technique used in case of unexpected instantaneous changes in the estimated parameter are newly proposed methods and can be applied for different problems. Throughout the study, the theory is supported by simulation results. First, each problem is examined individually and then it is demonstrated how the proposed solution technique can be integrated with the main idea: attitude determination and control for nanosatellite with magnetic sensors and actuators. The results show that the accuracy for a simple nanosatellite attitude determination and control system can be increased satisfactorily. The key findings presented in this study are published (or submitted) as international papers.

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