{"title":"大姿态角卫星运载火箭惯性平台控制研究","authors":"Yuan Cheng, J. Hung","doi":"10.1109/NAECON.1991.165778","DOIUrl":null,"url":null,"abstract":"In the case when a satellite launch vehicle is required to perform both large pitch and yaw angles in the coasting flight phase, one can utilize the programmed pitch around the outer gimbal axis of the platform and torquing the inner gimbal gyro simultaneously to realize it. In this case, it is not necessary to use the complicated four gimbal platform to fulfil the flight mission. The relationships between the vehicle's attitude angles are discussed in detail. The design scheme for implementation of stable-element precession is also presented.<<ETX>>","PeriodicalId":247766,"journal":{"name":"Proceedings of the IEEE 1991 National Aerospace and Electronics Conference NAECON 1991","volume":"81 1","pages":"0"},"PeriodicalIF":0.0000,"publicationDate":"1991-05-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":"{\"title\":\"On the control of the inertial platform for a satellite launch vehicle having large attitude angles\",\"authors\":\"Yuan Cheng, J. Hung\",\"doi\":\"10.1109/NAECON.1991.165778\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"In the case when a satellite launch vehicle is required to perform both large pitch and yaw angles in the coasting flight phase, one can utilize the programmed pitch around the outer gimbal axis of the platform and torquing the inner gimbal gyro simultaneously to realize it. In this case, it is not necessary to use the complicated four gimbal platform to fulfil the flight mission. The relationships between the vehicle's attitude angles are discussed in detail. The design scheme for implementation of stable-element precession is also presented.<<ETX>>\",\"PeriodicalId\":247766,\"journal\":{\"name\":\"Proceedings of the IEEE 1991 National Aerospace and Electronics Conference NAECON 1991\",\"volume\":\"81 1\",\"pages\":\"0\"},\"PeriodicalIF\":0.0000,\"publicationDate\":\"1991-05-20\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"0\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"Proceedings of the IEEE 1991 National Aerospace and Electronics Conference NAECON 1991\",\"FirstCategoryId\":\"1085\",\"ListUrlMain\":\"https://doi.org/10.1109/NAECON.1991.165778\",\"RegionNum\":0,\"RegionCategory\":null,\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"\",\"JCRName\":\"\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"Proceedings of the IEEE 1991 National Aerospace and Electronics Conference NAECON 1991","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.1109/NAECON.1991.165778","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"","JCRName":"","Score":null,"Total":0}
On the control of the inertial platform for a satellite launch vehicle having large attitude angles
In the case when a satellite launch vehicle is required to perform both large pitch and yaw angles in the coasting flight phase, one can utilize the programmed pitch around the outer gimbal axis of the platform and torquing the inner gimbal gyro simultaneously to realize it. In this case, it is not necessary to use the complicated four gimbal platform to fulfil the flight mission. The relationships between the vehicle's attitude angles are discussed in detail. The design scheme for implementation of stable-element precession is also presented.<>
京公网安备 11010802042870号
京ICP备2023020795号-1
分享
求助内容：
应助结果提醒方式：
扫码关注我们
