{"title":"新型导管飞行器的悬停控制","authors":"Peijun Liu, Hongbin Deng, Shikun Wang, Kewei Li, Yiran Wei","doi":"10.1109/ICUS48101.2019.8995931","DOIUrl":null,"url":null,"abstract":"In this paper, a new type of foldable winged unmanned aerial vehicle is designed, and the structure of the aircraft is analyzed. The dynamic model is established and an improved sliding mode control algorithm is used to control the attitude of the aircraft. In addition, a centroid position control method using attitude compensation is designed for the coupling characteristics of this aircraft. The simulation proves that the attitude and position of the new aircraft can be effectively controlled.","PeriodicalId":344181,"journal":{"name":"2019 IEEE International Conference on Unmanned Systems (ICUS)","volume":"12 1","pages":"0"},"PeriodicalIF":0.0000,"publicationDate":"2019-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":"{\"title\":\"Hover Control of New type ducted aircraft\",\"authors\":\"Peijun Liu, Hongbin Deng, Shikun Wang, Kewei Li, Yiran Wei\",\"doi\":\"10.1109/ICUS48101.2019.8995931\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"In this paper, a new type of foldable winged unmanned aerial vehicle is designed, and the structure of the aircraft is analyzed. The dynamic model is established and an improved sliding mode control algorithm is used to control the attitude of the aircraft. In addition, a centroid position control method using attitude compensation is designed for the coupling characteristics of this aircraft. The simulation proves that the attitude and position of the new aircraft can be effectively controlled.\",\"PeriodicalId\":344181,\"journal\":{\"name\":\"2019 IEEE International Conference on Unmanned Systems (ICUS)\",\"volume\":\"12 1\",\"pages\":\"0\"},\"PeriodicalIF\":0.0000,\"publicationDate\":\"2019-10-01\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"0\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"2019 IEEE International Conference on Unmanned Systems (ICUS)\",\"FirstCategoryId\":\"1085\",\"ListUrlMain\":\"https://doi.org/10.1109/ICUS48101.2019.8995931\",\"RegionNum\":0,\"RegionCategory\":null,\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"\",\"JCRName\":\"\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"2019 IEEE International Conference on Unmanned Systems (ICUS)","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.1109/ICUS48101.2019.8995931","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"","JCRName":"","Score":null,"Total":0}
In this paper, a new type of foldable winged unmanned aerial vehicle is designed, and the structure of the aircraft is analyzed. The dynamic model is established and an improved sliding mode control algorithm is used to control the attitude of the aircraft. In addition, a centroid position control method using attitude compensation is designed for the coupling characteristics of this aircraft. The simulation proves that the attitude and position of the new aircraft can be effectively controlled.
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