{"title":"星敏感器噪声水平未知时卫星动态模型对姿态估计精度的影响","authors":"H. Bolandi, F. F. Saberi","doi":"10.1109/ICCIAUTOM.2011.6356813","DOIUrl":null,"url":null,"abstract":"In this paper we will design an interacting multiple models adaptive attitude estimator (IMMAE) for a satellite with unknown star sensor noise level. This algorithm will be designed once using only kinematic model of the satellite which will be entitled 6-state IMMAE method and once using kinematic and dynamic models of the satellite which will be entitled 12-state IMMAE method. The results will be compared to illustrate the effect of dynamic model of satellite on accuracy of attitude estimation through numerical simulations. In this method, high fidelity gyro and star sensor models are used to evaluate the design in realistic situation associated with gyro errors and star sensor noise level uncertainties.","PeriodicalId":438427,"journal":{"name":"The 2nd International Conference on Control, Instrumentation and Automation","volume":"52 1","pages":"0"},"PeriodicalIF":0.0000,"publicationDate":"2011-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"3","resultStr":"{\"title\":\"Effect of dynamic model of satellite on accuracy of attitude estimation with unknown star sensor noise level\",\"authors\":\"H. Bolandi, F. F. Saberi\",\"doi\":\"10.1109/ICCIAUTOM.2011.6356813\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"In this paper we will design an interacting multiple models adaptive attitude estimator (IMMAE) for a satellite with unknown star sensor noise level. This algorithm will be designed once using only kinematic model of the satellite which will be entitled 6-state IMMAE method and once using kinematic and dynamic models of the satellite which will be entitled 12-state IMMAE method. The results will be compared to illustrate the effect of dynamic model of satellite on accuracy of attitude estimation through numerical simulations. In this method, high fidelity gyro and star sensor models are used to evaluate the design in realistic situation associated with gyro errors and star sensor noise level uncertainties.\",\"PeriodicalId\":438427,\"journal\":{\"name\":\"The 2nd International Conference on Control, Instrumentation and Automation\",\"volume\":\"52 1\",\"pages\":\"0\"},\"PeriodicalIF\":0.0000,\"publicationDate\":\"2011-12-01\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"3\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"The 2nd International Conference on Control, Instrumentation and Automation\",\"FirstCategoryId\":\"1085\",\"ListUrlMain\":\"https://doi.org/10.1109/ICCIAUTOM.2011.6356813\",\"RegionNum\":0,\"RegionCategory\":null,\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"\",\"JCRName\":\"\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"The 2nd International Conference on Control, Instrumentation and Automation","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.1109/ICCIAUTOM.2011.6356813","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"","JCRName":"","Score":null,"Total":0}
Effect of dynamic model of satellite on accuracy of attitude estimation with unknown star sensor noise level
In this paper we will design an interacting multiple models adaptive attitude estimator (IMMAE) for a satellite with unknown star sensor noise level. This algorithm will be designed once using only kinematic model of the satellite which will be entitled 6-state IMMAE method and once using kinematic and dynamic models of the satellite which will be entitled 12-state IMMAE method. The results will be compared to illustrate the effect of dynamic model of satellite on accuracy of attitude estimation through numerical simulations. In this method, high fidelity gyro and star sensor models are used to evaluate the design in realistic situation associated with gyro errors and star sensor noise level uncertainties.
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