{"title":"气动弹性飞行器飞行控制系统设计","authors":"F. Kubica, T. Livet","doi":"10.1109/CCA.1994.381445","DOIUrl":null,"url":null,"abstract":"The evolution of modern day aircraft increases the interaction between aeroelastic dynamics and control laws, known as aeroservoelasticity. An integrated flight control system without structural filters is proposed in order to achieve good handling qualities and increase structural mode damping. In the first step sensor and actuator location is studied, and in a second step the use of the linear quadratic regulator with output feedback for the synthesis of the control law.<<ETX>>","PeriodicalId":173370,"journal":{"name":"1994 Proceedings of IEEE International Conference on Control and Applications","volume":"93 1","pages":"0"},"PeriodicalIF":0.0000,"publicationDate":"1994-08-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"5","resultStr":"{\"title\":\"Design of flight control system for an aeroelastic aircraft\",\"authors\":\"F. Kubica, T. Livet\",\"doi\":\"10.1109/CCA.1994.381445\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"The evolution of modern day aircraft increases the interaction between aeroelastic dynamics and control laws, known as aeroservoelasticity. An integrated flight control system without structural filters is proposed in order to achieve good handling qualities and increase structural mode damping. In the first step sensor and actuator location is studied, and in a second step the use of the linear quadratic regulator with output feedback for the synthesis of the control law.<<ETX>>\",\"PeriodicalId\":173370,\"journal\":{\"name\":\"1994 Proceedings of IEEE International Conference on Control and Applications\",\"volume\":\"93 1\",\"pages\":\"0\"},\"PeriodicalIF\":0.0000,\"publicationDate\":\"1994-08-24\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"5\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"1994 Proceedings of IEEE International Conference on Control and Applications\",\"FirstCategoryId\":\"1085\",\"ListUrlMain\":\"https://doi.org/10.1109/CCA.1994.381445\",\"RegionNum\":0,\"RegionCategory\":null,\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"\",\"JCRName\":\"\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"1994 Proceedings of IEEE International Conference on Control and Applications","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.1109/CCA.1994.381445","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"","JCRName":"","Score":null,"Total":0}
Design of flight control system for an aeroelastic aircraft
The evolution of modern day aircraft increases the interaction between aeroelastic dynamics and control laws, known as aeroservoelasticity. An integrated flight control system without structural filters is proposed in order to achieve good handling qualities and increase structural mode damping. In the first step sensor and actuator location is studied, and in a second step the use of the linear quadratic regulator with output feedback for the synthesis of the control law.<>
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