大姿态角卫星运载火箭惯性平台控制研究

Proceedings of the IEEE 1991 National Aerospace and Electronics Conference NAECON 1991 Pub Date : 1991-05-20 DOI:10.1109/NAECON.1991.165778

Yuan Cheng, J. Hung

{"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}

引用次数: 0

摘要

当卫星运载火箭在滑行飞行阶段需要同时执行大俯仰和偏航角时，可以利用围绕平台外框架轴的编程俯仰并同时扭转内框架陀螺仪来实现。在这种情况下，没有必要使用复杂的四万向节平台来完成飞行任务。详细讨论了飞行器姿态角之间的关系。文中还提出了实现稳定元进动的设计方案。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

查看原文本刊更多论文

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.<>

求助全文

通过发布文献求助，成功后即可免费获取论文全文。去求助

来源期刊

Proceedings of the IEEE 1991 National Aerospace and Electronics Conference NAECON 1991

自引率

0.00%

发文量