{"title":"Loris立方体卫星姿态确定与控制系统的研制","authors":"Anna Wailand, R. Bauer","doi":"10.32393/csme.2021.32","DOIUrl":null,"url":null,"abstract":"— The Low Earth Orbit Reconnaissance Imagery Satellite (LORIS) is a 2U Earth-observation CubeSat in development at Dalhousie University. This paper describes the proposed attitude determination and control system (ADCS) for this CubeSat. Attitude determination is carried out using the Quaternion ESTimation (QUEST) algorithm in combination with an extended Kalman filter that propagates an internal dynamic model of the CubeSat. A control approach is then proposed that cycles between reaction wheel nadir-pointing control during portions of the orbit when a Sun vector can be estimated, and magnetic detumbling for reaction wheel desaturation during portions of the orbit where Earth eclipses Sun. Computer simulations are then presented to validate the proposed ADCS.","PeriodicalId":446767,"journal":{"name":"Progress in Canadian Mechanical Engineering. Volume 4","volume":"33 1","pages":"0"},"PeriodicalIF":0.0000,"publicationDate":"2021-06-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":"{\"title\":\"Development Of An Attitude Determination And Control System For The Loris Cubesat\",\"authors\":\"Anna Wailand, R. Bauer\",\"doi\":\"10.32393/csme.2021.32\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"— The Low Earth Orbit Reconnaissance Imagery Satellite (LORIS) is a 2U Earth-observation CubeSat in development at Dalhousie University. This paper describes the proposed attitude determination and control system (ADCS) for this CubeSat. Attitude determination is carried out using the Quaternion ESTimation (QUEST) algorithm in combination with an extended Kalman filter that propagates an internal dynamic model of the CubeSat. A control approach is then proposed that cycles between reaction wheel nadir-pointing control during portions of the orbit when a Sun vector can be estimated, and magnetic detumbling for reaction wheel desaturation during portions of the orbit where Earth eclipses Sun. Computer simulations are then presented to validate the proposed ADCS.\",\"PeriodicalId\":446767,\"journal\":{\"name\":\"Progress in Canadian Mechanical Engineering. Volume 4\",\"volume\":\"33 1\",\"pages\":\"0\"},\"PeriodicalIF\":0.0000,\"publicationDate\":\"2021-06-27\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"0\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"Progress in Canadian Mechanical Engineering. Volume 4\",\"FirstCategoryId\":\"1085\",\"ListUrlMain\":\"https://doi.org/10.32393/csme.2021.32\",\"RegionNum\":0,\"RegionCategory\":null,\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"\",\"JCRName\":\"\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"Progress in Canadian Mechanical Engineering. Volume 4","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.32393/csme.2021.32","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"","JCRName":"","Score":null,"Total":0}
Development Of An Attitude Determination And Control System For The Loris Cubesat
— The Low Earth Orbit Reconnaissance Imagery Satellite (LORIS) is a 2U Earth-observation CubeSat in development at Dalhousie University. This paper describes the proposed attitude determination and control system (ADCS) for this CubeSat. Attitude determination is carried out using the Quaternion ESTimation (QUEST) algorithm in combination with an extended Kalman filter that propagates an internal dynamic model of the CubeSat. A control approach is then proposed that cycles between reaction wheel nadir-pointing control during portions of the orbit when a Sun vector can be estimated, and magnetic detumbling for reaction wheel desaturation during portions of the orbit where Earth eclipses Sun. Computer simulations are then presented to validate the proposed ADCS.
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