{"title":"Adaptive Attitude Control for Spinning Projectiles With Time-Varying Aerodynamic Uncertainties","authors":"Zhongjiao Shi;Zhijie Liu;Feng Han;Xinchun Wang","doi":"10.1109/TAES.2025.3541607","DOIUrl":null,"url":null,"abstract":"Most gun-launched guided projectiles adopt a spinning airframe to simplify the control structure and improve stability. However, the cross-coupling effects of inertia, aerodynamics, and control caused by spinning increase the difficulty of the autopilot design. This article proposes an adaptive attitude autopilot design method for a class of spinning projectiles with time-varying aerodynamic uncertainties. First, a fully actuated attitude dynamic model of the pitch/yaw channel for a spinning projectile is established, in which the aerodynamic force/moment are regarded as time-varying uncertainties. Second, an adaptive attitude autopilot is proposed by combining fully actuated system theory and adaptive control theory to restore the linear characteristics of the closed-loop system. Then, a parameter-safe adaptive law is presented using control barrier functions to ensure the boundedness of estimation parameters and improve the robustness of the closed-loop system. Finally, comparative numerical simulations are performed to demonstrate that the proposed attitude control method can guarantee the boundedness of both the tracking error and estimation error.","PeriodicalId":13157,"journal":{"name":"IEEE Transactions on Aerospace and Electronic Systems","volume":"61 4","pages":"8099-8111"},"PeriodicalIF":5.7000,"publicationDate":"2025-02-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":null,"platform":"Semanticscholar","paperid":null,"PeriodicalName":"IEEE Transactions on Aerospace and Electronic Systems","FirstCategoryId":"94","ListUrlMain":"https://ieeexplore.ieee.org/document/10884865/","RegionNum":2,"RegionCategory":"计算机科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"Q1","JCRName":"ENGINEERING, AEROSPACE","Score":null,"Total":0}
引用次数: 0
Abstract
Most gun-launched guided projectiles adopt a spinning airframe to simplify the control structure and improve stability. However, the cross-coupling effects of inertia, aerodynamics, and control caused by spinning increase the difficulty of the autopilot design. This article proposes an adaptive attitude autopilot design method for a class of spinning projectiles with time-varying aerodynamic uncertainties. First, a fully actuated attitude dynamic model of the pitch/yaw channel for a spinning projectile is established, in which the aerodynamic force/moment are regarded as time-varying uncertainties. Second, an adaptive attitude autopilot is proposed by combining fully actuated system theory and adaptive control theory to restore the linear characteristics of the closed-loop system. Then, a parameter-safe adaptive law is presented using control barrier functions to ensure the boundedness of estimation parameters and improve the robustness of the closed-loop system. Finally, comparative numerical simulations are performed to demonstrate that the proposed attitude control method can guarantee the boundedness of both the tracking error and estimation error.
期刊介绍:
IEEE Transactions on Aerospace and Electronic Systems focuses on the organization, design, development, integration, and operation of complex systems for space, air, ocean, or ground environment. These systems include, but are not limited to, navigation, avionics, spacecraft, aerospace power, radar, sonar, telemetry, defense, transportation, automated testing, and command and control.