{"title":"利用无模型自适应控制为三级卫星运载器设计新颖的综合制导和控制装置","authors":"Mohammadreza Yaseri, Alireza Basohbat Novinzadeh","doi":"10.1177/09544100221107507","DOIUrl":null,"url":null,"abstract":"A model-free adaptive control is proposed for suboptimal guidance correction and control of a prototypical three-stage satellite carrier. For this sake, we consider a nominal guidance for the model of the system and design the adaptive control for a single-input multi-output system exposed to wind disturbance and measurement noise in the rates of inputs and outputs. Then, subsequent to the guidance correction, a differentiation model of the system is estimated and the control policy is realized under some profitable performance constraints to set the satellite in a desirable circular orbit. The simulation results readily reveal the efficiency of the proposed method and its robustness to uncertainties in the system.","PeriodicalId":54566,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering","volume":"26 1","pages":""},"PeriodicalIF":1.0000,"publicationDate":"2024-03-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":"{\"title\":\"Novel integrated guidance and control design for a three-stage satellite carrier using model-free adaptive control\",\"authors\":\"Mohammadreza Yaseri, Alireza Basohbat Novinzadeh\",\"doi\":\"10.1177/09544100221107507\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"A model-free adaptive control is proposed for suboptimal guidance correction and control of a prototypical three-stage satellite carrier. For this sake, we consider a nominal guidance for the model of the system and design the adaptive control for a single-input multi-output system exposed to wind disturbance and measurement noise in the rates of inputs and outputs. Then, subsequent to the guidance correction, a differentiation model of the system is estimated and the control policy is realized under some profitable performance constraints to set the satellite in a desirable circular orbit. The simulation results readily reveal the efficiency of the proposed method and its robustness to uncertainties in the system.\",\"PeriodicalId\":54566,\"journal\":{\"name\":\"Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering\",\"volume\":\"26 1\",\"pages\":\"\"},\"PeriodicalIF\":1.0000,\"publicationDate\":\"2024-03-27\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"0\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering\",\"FirstCategoryId\":\"5\",\"ListUrlMain\":\"https://doi.org/10.1177/09544100221107507\",\"RegionNum\":4,\"RegionCategory\":\"工程技术\",\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"Q3\",\"JCRName\":\"ENGINEERING, AEROSPACE\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering","FirstCategoryId":"5","ListUrlMain":"https://doi.org/10.1177/09544100221107507","RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"Q3","JCRName":"ENGINEERING, AEROSPACE","Score":null,"Total":0}
Novel integrated guidance and control design for a three-stage satellite carrier using model-free adaptive control
A model-free adaptive control is proposed for suboptimal guidance correction and control of a prototypical three-stage satellite carrier. For this sake, we consider a nominal guidance for the model of the system and design the adaptive control for a single-input multi-output system exposed to wind disturbance and measurement noise in the rates of inputs and outputs. Then, subsequent to the guidance correction, a differentiation model of the system is estimated and the control policy is realized under some profitable performance constraints to set the satellite in a desirable circular orbit. The simulation results readily reveal the efficiency of the proposed method and its robustness to uncertainties in the system.
期刊介绍:
The Journal of Aerospace Engineering is dedicated to the publication of high quality research in all branches of applied sciences and technology dealing with aircraft and spacecraft, and their support systems. "Our authorship is truly international and all efforts are made to ensure that each paper is presented in the best possible way and reaches a wide audience.
"The Editorial Board is composed of recognized experts representing the technical communities of fifteen countries. The Board Members work in close cooperation with the editors, reviewers, and authors to achieve a consistent standard of well written and presented papers."Professor Rodrigo Martinez-Val, Universidad Politécnica de Madrid, Spain
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