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Adaptive Asynchronous control for USVs Over Jointly Connected Switching Topologies and Event-Triggered Communication

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IEEE Transactions on Industrial Informatics 2025年

作者： Yu, Kunting Li, Yongming Lv, Maolong Tong, Shaocheng Dalian Maritime University Navigation College Dalian116026 China Liaoning University of Technology College of Science Liaoning 121001 China Air Force Engineering University National Key Laboratory of Unmanned Aerial Vehicle Technology National Key Lab of Aerospace Power System and Plasma Technology The College of Air Traffic Control and Navigation Xi'an710051 China

This article delves into the adaptive event-triggered control approach for a fleet of underactuated unmanned surface vehicles (USVs) that are interconnected through shared switching topologies. The methodology put forth addresses the asynchronous control challenge within this networked framework. By incorporating an event-triggered mechanism, we have crafted the distributed asynchronous observers to approximate the reference signal, capitalizing on the dynamics of distributed errors. Leveraging fuzzy logical systems, we have devised control inputs for the underactuated USVs by employing the backstepping technique. Utilizing Lyapunov stability theory, we have rigorously demonstrated that these control inputs facilitate tracking of the reference signal by the USVs, contingent upon their relative positions. This article concludes with a validation of the proposed control strategy, showcasing its effectiveness in practical scenarios. © 2005-2012 IEEE.

关键词： Unmanned surface vehicles

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Design and Flight Test of a Compact and Rapidly-Deployable Air-Launched Inflatable-Winged Aircraft

Design and Flight Test of a Compact and Rapidly-Deployable A...

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AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025

作者： Ge, Hang Xu, Yixiang Sun, Donglei Chen, Xinmin Chen, Boyang School of Aerospace Faculty of Science and Engineering University of Nottingham Ningbo China Zhejiang Ningbo315100 China Department of Mechanical Materials and Manufacturing Engineering UNNC-NFTZ Blockchain Laboratory University of Nottingham Ningbo China Zhejiang Ningbo315100 China Advanced Intelligent Manufacturing Research Group Control System Lab University of Nottingham Ningbo China Zhejiang Ningbo315100 China Zhejiang Provincial Engineering Research Center of Special Aircraft Ningbo Institute of Materials Technology & Engineering Chinese Academy of Sciences Zhejiang Ningbo315100 China

ISBN: (数字)9781624107238

ISBN: (纸本)9781624107238

In this research, a high-altitude, compact and rapidly deployable, air-launched, inflatablewinged aircraft is designed, developed, and flight-tested to investigate the flight characteristics of inflatable-winged aircraft as well as the in-flight inflation and dynamic deployment properties when launched from various carriers. To start with, two types of inflatable wings employing different materials have been designed, fabricated, and tested, the tests including structural characteristics tests, inflation properties tests, and low-Reynolds-number wind-tunnel tests. A full-scale 30-kilogram prototype unmanned aerial vehicle with inflatable wings was then designed, assembled and tested with some basic low-altitude flights to verify the feasibility of the aerodynamic layout and the trim and stability and control characteristics. Finally, low- and high-altitude in-flight launches will be conducted to study the dynamic deployment properties and high-altitude flight characteristics of this design. © 2025, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： Wind tunnels

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A Self-Calibration Method based on One-Time Electrification before Launching for Inertial Navigation system 7

A Self-Calibration Method based on One-Time Electrification ...

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2016 IEEE Chinese Guidance, Navigation and control Conference (IEEE CGNCC2016)

作者： XIANG Gang QIU Feng MIAO Jing DUAN Ran National Key Lab on Aerospace Intelligent Control Beijing Aerospace Automatic Control Institute Beijing Institute of Electronic System Engineering

ISBN: (纸本)9781467383196

The measuring error of Inertial Navigation system(INS) is the main fact that affects the hitting accuracy of inertial-guided *** parameters compensation could get *** of all,this article builds an error model of gyro and accelerometer,and then in order to achieve these error parameters' value as closely as possible to their true value in application,a quick self-calibration method based on one-time electrification before launching for inertial platform is *** this method,INS rotates to 9 particular positions,outputs of inertial sensors are collected in drift state and each error parameter can be *** self-calibration method requires no additional devices,improving the maneuverability of the whole ***,experiments are carried out using both the self-calibration method and unit calibration method,the two methods' results show that the largest compared accuracy is 9.40%,which demonstrates the practicability and validity of the suggested method.

关键词： frame INS A Self-Calibration Method based on One-Time Electrification before Launching for Inertial Navigation system

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Model Based Automatic control Design for the T-FLEX Demonstrator Using RCE Environment

Model Based Automatic Control Design for the T-FLEX Demonstr...

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AIAA SciTech Forum and Exposition, 2023

作者： Takarics, Béla Patartics, Bálint Luspay, Tamás Vanek, Bálint Poussot-Vassal, Charles Vuillemin, Pierre Wüstenhagen, Matthias Systems and Control Lab Institute for Computer Science and Control Budapest1111 Hungary Onera - The French Aerospace Lab ToulouseF-31055 France Department of System Dynamics and Control DLR - Institute of System Dynamics and Control Wessling82234 Germany

ISBN: (数字)9781624106996

ISBN: (纸本)9781624106996

The main goal of the paper is to develop automatic control design methods for flexible aircraft. The motivation for the research is that such automatic control generation enables the inclusion of the control design algorithms into the multidisciplinary design optimization (MDO) of aircraft design. In such an extended MDO framework, called co-design, the sizing, structural dynamics, aerodynamics and the controllers of the aircraft are optimized in one single step. This way control technologies can be included early-on in the preliminary design stage of aircraft design. Since the control design is model based, first a control oriented aeroservoelastic (ASE) model needs to be developed. The modeling is done via the bottomup modelling approach. The model generation also needs to be automatic due to parameter changes resulting from the MDO process. The research focuses on flexible aircraft, therefore, the control algorithms include baseline, manoeuvre load alleviation, gust load alleviation and flutter suppression controllers. All of these algorithms needs to be developed in such way that they can automatically executed in the MDO process. The overall MDO framework is implemented in the Remote Component Environment (RCE) and the aircraft investigated is the T-Flex demonstrator of the FLIPASED project. The paper presents the main concepts of the modeling and control synthesis, analysis for the above mentioned four controllers and the most important aspects of integrating such automatic control design methods into the RCE environment. © 2023, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： controllers

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Limit-cycles prevention via multiple H∞ constraints with an application to anti-windup design

Limit-cycles prevention via multiple H∞ constraints with an...

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9th IFAC Symposium on Nonlinear control systems, NOLCOS 2013

作者： Biannic, Jean-Marc ONERA French Aerospace Lab. System Control Flight Dynamics Department F-31055 Toulouse Cedex France

ISBN: (纸本)9783902823472

Rate and magnitude control limitations are often responsible for the apparition of undesired limit-cycles in the resulting nonlinear closed-loop system. Based on the well- known describing function approach, it is shown in this paper that such limit cycles can be avoided as soon as H∞ constraints are simultaneously satisfied by appropriately chosen linear interconnections. This result is then used to design anti-windup compensators. © IFAC.

关键词： Nonlinear control systems

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Tailoring intermetallics via cellular boundary enables strong yet ductile property: An example in Gd-enriched neutron shielding alloys

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Scripta Materialia 2025年 265卷

作者： Hou, Kunlei He, Suyun Wei, Boxin Cui, Luqing Zang, Yihu Zhao, Peng Liang, Tian Ma, Guangcai Ma, Yingche Institute of Metal Research Chinese Academy of Sciences Shenyang110016 China CAS Key Laboratory of Nuclear Materials and Safety Assessment Institute of Metal Research Chinese Academy of Sciences Shenyang110016 China Tianjin Key Laboratory of Materials Laminating Fabrication and Interface Control Technology School of Materials Science and Engineering Hebei University of Technology Tianjin300401 China National Key Lab of Aerospace Power System and Plasma Technology Xi'an Jiaotong University Xi'an710049 China School of Mechanical Engineering Xi'an Jiaotong University Xi'an710049 China Department of Physics and Astronomy University of California Irvine IrvineCA92697 United States

Gd is a highly effective element for neutron shielding, but its minimal solubility promotes Gd-rich intermetallics that degrade alloy properties if not properly controlled. This study introduces an innovative approach to refine these intermetallics to a sub-micron scale and achieve a uniform distribution by leveraging the cellular boundaries formed during laser powder bed fusion. These cellular boundaries, combined with the tailored intermetallics, act as "modulators" that effectively impede plastic deformation while permitting dislocation motion, resulting in a satisfying strength-ductility synergy. The findings offer a promising direction for incorporating elements with low solubility but functional properties by tailoring intermetallics through cellular boundary engineering. © 2025 The Author(s)

关键词： Intermetallics

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Alflex five degrees of freedom hanging flight test 22nd

Alflex five degrees of freedom hanging flight test

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22nd Atmospheric Flight Mechanics Conference, 1997

作者： Tsukamoto, Taro Yanagihara, Masaaki Nagayasu, Masahiko Sagisaka, Masakazu National Aerospace Laboratory Control System Division Tokyo Japan National Aerospace Laboratory Guidance and Control Lab Tokyo Japan National Spece Development Agency of Japan Winged Space Vehicle Office Tokyo Japan

The National aerospace laboratory (NAL) and the National Space Development Agency of Japan (NASDA), cooperating in the research and development of an unmanned reentry vehicle named HOPE (H-II Orbiting Plane), conducted a series of automatic landing flight experiments (ALFLEX). In the ALFLEX project, several constrained flight tests using gimbal support system were conducted before the first automatic landing trial. The purposes of these tests were to confirm the function and performance of the vehicle's control system and its aerodynamic characteristics. In this paper, the stability and performance of the flight control system are studied. In steady or quasi-static flight tests, the vehicle attitude was well stabilized around the trimmed condition. The step command responses for angle of attack, side slip angle, and roll angle were consistent with simulation results. © 1997, American Institute of Aeronautics and Astronautics, Inc.

关键词： Flight control systems

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Design of an Image Motion Compensation (IMC) algorithm for the Communication, Ocean, Meteorological Satellite (COMS)

Design of an Image Motion Compensation (IMC) algorithm for t...

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AIAA/AAS Astrodynamics Specialist Conference, 2006

作者： Jung, Taek-Seo Lee, Un-Seob Park, Sang-Young Choi, Yoon-Hyuk Bang, Hyo-Choong Ju, Gwanghyeok Yang, Koon-Ho Yonsei University Seoul 120-749 Korea Republic of Korea Advanced Institute of Science and Technology Daejeon 305-701 Korea Republic of Korea Aerospace Research Institute Daejeon 305-333 Korea Republic of Astrodynamics and Control Lab. Dept. of Astronomy and Space Science Flight Dynamics and Control Lab. Dept. of Aerospace Engineering Communication Satellite System Department

ISBN: (纸本)1563478226

This paper presents an Image Motion Compensation (IMC) algorithm for Korea's Communication, Ocean, and Meteorological Satellite (COMS). An IMC algorithm is a priority component of the Image Navigation and Registration (INR) system to locate and register radiometric image data. To eliminate image distortions, depointing of the imager aiming direction must be adjusted. A compensation algorithm to correct depointing caused by satellite motion is designed, and the capability of the algorithm is compared with that of existing algorithm applied to the GOES's INR system. The algorithm developed in this paper improves pointing accuracy by efficiently compensating for depointing of the imager aiming direction. Copyright © 2006 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： Motion compensation

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An airborne Position and Orientation system (POS) for remote sensing and its current state

An airborne Position and Orientation System (POS) for remote...

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2017 IEEE International Conference on Imaging systems and Techniques, IST 2017

作者： Zhai, Fengguang Jianli, Li Ye, Wen Gu, Bin Lu, Zhaoxing Qiu, Haitao School of Instrumentation Science and Opto-electronics Engineering Beihang University Beijing China Beijing Institute of Aerospace Control Devices Beijing China National Key Lab of Satellite Navigation System and Equipment Technology Shijiazhuang China

ISBN: (纸本)9781538616208

The airborne Position and Orientation system (POS) is vital shared equipment, and plays an important role in aerial survey and remote sensing system. It achieves the ability to a direct georeferencing for typical optical camera flash imaging system, and to motion compensation for typical SAR integral imaging system, further improves image quality and efficiency of airborne imaging sensors. In this article, the components and operation principles of POS are summarized. The survey of airborne POS and the development trends of aerial survey and remote sensing system are introduced and analyzed. These analyses can provide reference for development of high-precision airborne POS technologies for aerial survey and remote sensing system. © 2017 IEEE.

关键词： Motion compensation

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Modelling of the 3-Dof nonlinear aircraft behaviour via small standard forms

Modelling of the 3-Dof nonlinear aircraft behaviour via smal...

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26th Congress of International Council of the Aeronautical Sciences 2008, ICAS 2008

作者： Döll, Carsten Berard, Caroline ONERA The French Aerospace Lab Department of System Control and Flight Dynamics 2 av Edouard Belin BP 4025 F-31055 Tolouse France The French Institute for Aeronautics Department of Control 10 av Edouard Belin BP 4032 F-31055 Tolouse France

ISBN: (纸本)9781605607153

The objective of this paper is to illustrate that the standard form or Linear Fractional Transformation LFT framework is a unique and powerful framework to treat with nonlinear aircraft behaviour during flight control law synthesis and analysis. Within this paper, a precise and as small as possible LFT for a nonlinear 3-DOF aircraft with time varying parameters is derived. This LFT is validated both in a linear and nonlinear framework 1.

关键词： Linear transformations

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