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AIAA SciTech Forum

作者： Milz, Daniel May, Marc Looye, Gertjan German Aerosp Ctr DLR Inst Syst Dynam & Control Dept Aircraft Syst Dynam D-82234 Wessling Germany

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

Transformational electric vertical take-off and landing (eVTOL) vehicles, including tiltwings, have (re)gained popularity over the past decade owing to their advantages of efficient wing-borne cruise flight and reduced requirements on ground-based infrastructure. They promise a new mode of transportation for fast and versatile, short-to-medium-haul on-demand connections. However, they come at the cost of complex mechanics, flight dynamics, and aerodynamics. Among these factors, the different flight regimes and the transition between them make the control system design challenging. Ideally, a flight control system provides means for pilot interaction, autoflight functions, robustness to disturbances, and failure mitigation. The different flight regimes with distinct flight dynamics in a single vehicle motivate a holistic approach. So far, no control approach has prevailed, which raises the question of how to design a control concept that satisfies the above requirements for the full flight envelope. To solve this problem, we derive a generalized representation for transformational eVTOLs and propose a flight control approach for this system, consisting of a dynamic-inversion-based angular rate and velocity control law. Moreover, combining these control functions with optimization-based control allocation is motivated and presented. Finally, the concept is applied to a tandem tilt-wing configuration and analyzed. Results suggest the practicability of the proposed control approach.

关键词： Closed Loop control Aircraft Flight Dynamics Aerodynamic Coefficients Electric Vertical Take off and Landing Flight control design Wing Configurations Cruise Flight Flight Envelope control system design Fixed Wing Aircraft

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Airship Flight Model Creation: A Computational Approach for High Altitude Pseudo-Satellites (HAPS)

Airship Flight Model Creation: A Computational Approach for ...

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AIAA SciTech Forum

作者： Aboelezz, Ahmed Escarcega, Mario Herkenhoff, Brenden Pozhanka, Yan Doyle, Tyler Hassanalian, Mostafa New Mexico Inst Min & Technol Dept Mech Engn Socorro NM 87801 USA Sceye Inc Moriarty NM 87035 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

This paper presents a comprehensive, innovative approach to generating an airship nonlinear model tailored for High Altitude Pseudo-Satellites (HAPS). To achieve this purpose a scaled model of the airship was made to be tested and validate the mathematical modeling of the airship. In the first part of our research, we focus on the development of a Computational Fluid Dynamics (CFD) results to obtain the aerodynamics data needed for the simulation. This computational tool is based on vortices lattice method (VLM). The generated data encompasses forces for nonlinear simulations, aerodynamic coefficients for nonlinear simulations. These parameters are essential for the accurate modeling of airships and directly influence the stability, control, and overall performance of HAPS. The second part of our research involves the creation of an intricate airship model. We develop a code that produces the airship equation of motion model and state space model sing Simulink. This process involves the integration of the aerodynamic and weight data into a comprehensive airship model. This model is subsequently used in control simulations, forming the basis for designing and testing the control systems. The successful generation of detailed aerodynamic and weight data and the creation of a comprehensive airship model provide a robust foundation for future advancements in HAPS control and propulsion systems. Our methodology promises to enhance the efficiency, reliability, and performance of high-altitude platforms, contributing significantly to the aerospace industry. This research signifies a significant step forward in the field of high-altitude flight mechanics and control. The findings and methodologies developed through this work have the potential to influence the future design and operation of HAPS, driving advancements in the field and contributing to the realization of more efficient and effective high-altitude platforms.

关键词： Satellites High Altitude Airships Aerodynamic Coefficients control system design Computational Fluid Dynamics Propulsion system Simulink Aerospace Industry Flight Mechanics Mathematical Models

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Robust control system Against Temperature Variance for Space-Use Shape-Memory-Alloy Actuators

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JOURNAL OF SPACECRAFT AND ROCKETS 2022年第4期59卷 1062-1073页

作者： Nozaki, Manato Miyata, Kikuko Hara, Susumu Otsuki, Masatsugu Nagoya Univ Dept Aerosp Engn Grad Sch Engn Chikusa Ku Furo Cho Nagoya Aichi 4648603 Japan Meijo Univ Dept Aerosp Engn Grad Sch Engn Chikusa Ku Furo Cho Nagoya Aichi 4688502 Japan Japan Aerosp Explorat Agcy Dept Spacecraft Engn Inst Space & Astronaut Sci Sagamihara Kanagawa 2525210 Japan

Shape-memory alloys (SMAs), well-known as the force source in space-use nonexplosive actuators, generate force through temperature-based phase transitions. The force amount is related to the volume and mass of the SMA. This study presents a method to improve the force generation profile of the SMA actuator, which consists of an SMA tube, a mechanical restraint, and a heater. The high ratio of force output to mass allows for the SMA actuator to achieve a high energy density;however, its force trajectories are affected by the environmental temperature variance because of its huge heat capacity. The uncertainties of the force trajectories limit the applications of the actuator. This paper proposes a method to achieve the required force trajectories under temperature variance to enlarge the application of the high-energy-density SMA actuators. In addition, a suitable model is established for the force trajectory control method based on the thermomechanical coupling response characteristics. A thermal balance model is constructed under a vacuum environment. Furthermore, a hysteresis characteristic model of the phase transformation is introduced, and it reduces the heating profile limitation. The SMA's generation force trajectory is designed based on the model predictive control method. The designed trajectory is realized using a simple temperature measurement feedback control method based on the proportional-integral-derivative method. To illustrate the system design, the holding-release mechanism application is selected. The effectiveness of the proposed methods is verified through specific test piece system identification and control simulations, which are performed both numerically and experimentally under temperature variance.

关键词： Actuators SMA control system design Proportional Integral Derivative Feedback control system Energy Density Hysteresis Heat Capacity Martensite Numerical Simulation

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control of a DFIG based wind turbine using modified Conditional Servo-compensator 22

Control of a DFIG based wind turbine using modified Conditio...

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22nd World Congress of the International Federation of Automatic control (IFAC)

作者： Van Cuong Nguyen Netto, Mariana Damm, Gilney Paris Saclay Univ L2S Gif Sur Yvette France Univ Gustave Eiffel COSYS PICS L IFSTTAR F-78000 Versailles France Univ Gustave Eiffel COSYS IMSE IFSTTAR F-77447 Marne La Vallee France

ISBN: (纸本)9781713872344

This paper presents the control of a wind turbine composed by a doubly fed induction generator (DFIG), which provides power to the main grid through a feeder. The control algorithm is designed following the modified Conditional Servo-Compensator (mCS) theory. This control technique was recently developed to a broad class of nonlinear systems, and this paper brings the first result applied to wind turbines. The mCS theory has several advantages compared to others, as it is a robust nonlinear control scheme. First, it provides rigorous stability analysis, that allows explicit definition of performance and operating conditions. Secondly, it is a robust controller, and only needs lump values and bounds for parameters and dynamics. Finally it is very simple and easy to implement, and does not need heavy computer burden, it is only based on standard local measurements, and represents a promising solution for real applications. The theoretical results are verified by simulations using detailed Simpower models. These simulations show very good results facing a Low Voltage Ride Through scenario, which is one of the most severe tests used for practical applications. The proposed scheme could easily be adapted to the control of other applications based on power converters, as the control of the interconnection of a full wind farm to the main grid, or the control of a terminal in a DC grid.

关键词： control of renewable energy resources control of power systems Nonlinear control Application of power electronics control system design

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Station-Keeping of L2 Halo Orbits Under Sampled-Data Model Predictive control

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JOURNAL OF GUIDANCE control AND DYNAMICS 2022年第7期45卷 1337-1346页

作者： Elobaid, Mohamed Mattioni, Mattia Monaco, Salvatore Normand-Cyrot, Dorothee Sapienza Univ Rome Dept Comp Control & Management Engn Via Ariosto 25 I-00185 Rome Italy Sapienza Univ Rome L2S Via Ariosto 25 I-00185 Rome Italy Univ Paris Saclay CNRS Cent Supelec Lab Signals & SystL2SUMR 8506 3 Rue Joliot Curie F-91192 Gif Sur Yvette France

The dynamics of a spacecraft in the Earth–moon gravitational system involving the restricted three-body problem [RTBP] exhibit equilibria commonly known as libration or Lagrangian points. Researchers provide a new control scheme assuming the elliptic RTBP model under the influence of SRP that captures the principal feature of the dynamics while retaining simplicity. A modified model predictive control (MPC) approach is also proposed to cope with real-time implementation issues as, such as the digital nature of both actuation and sensing and possible limits on control, unavoidable in practice. Researchers specifically consider the case in which measures are available only at sporadic time instants, whereas the control is piecewise constant over the sampling period. The proposed approach is based on the design of multirate (MR) strategies at the planning level providing a suitable reference governor for an MPC control scheme.

关键词： Model Predictive control Halo Orbit Earth Feedback Linearization Lagrangian Point Satellites Nonlinear Programming MATLAB control system design Quadratic Programming

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Dynamic response and control of the molten zone in laser heated pedestal growth 34

Dynamic response and control of the molten zone in laser hea...

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2025 Conference on Solid State Lasers

作者： Peoples, J. A. Martinez, A. D. Gray, B. A. US Air Force Res Lab Mat & Mfg Directorate Wright Patterson AFB OH 45433 USA Riverside Res Inst 2316 Natl Beavercreek OH 45324 USA

ISBN: (纸本)9781510684300;9781510684317

This study provides a comprehensive framework for understanding and controlling the dynamic behavior of the molten zone in laser heated pedestal growth. Using a second-order dynamic model, the system's frequency response is analyzed to derive key parameters, including sensitivity and responsiveness, as functions of melt geometry and operational variables. This approach reveals the critical role of oscillatory dynamics and damping behavior in governing molten zone stability, with diameter reduction ratio and draw velocity identified as primary factors influencing system performance. Geometric models derived from experimental data form the foundation of an adaptive control strategy that leverages real-time monitoring via machine vision tools to dynamically stabilize the molten zone and mitigate disturbances. The findings of this study provide insights into the dynamic behavior of the laser heated pedestal growth system and offer a pathway for developing advanced control strategies to improve the stability, consistency, and automation of the process.

关键词： Laser heated pedestal growth (LHPG) Molten zone dynamics Single crystal fiber (SCF) Frequency response analysis Gain Time constant Machine vision control system design

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A Robust control Framework for Ensuring Stability and Efficiency in Microgrid Integration 4

A Robust Control Framework for Ensuring Stability and Effici...

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4th International Conference on Advances in Electrical, Computing, Communication and Sustainable Technologies, ICAECT 2024

作者： Baghel, Rahul Sahu, Rajendra Kumar Sharma, Nimmi Manju Kumar, Santosh Gupta, Pritha Kalinga University Department of Ee Chhattisgarh Raipur India Government Engineering College Department of Ee Bihar Jehanabad India Gaya College of Engineering Department of Eee Bihar India Bhilai Institute of Technology Department of Ee Chhattisgarh Durg India

ISBN: (纸本)9798350343670

Microgrid integration presents special difficulties for reliable and effective operation, which calls for the creation of complex control systems. This article explains how to create and put into place a reliable control system using MATLAB/Simulink, enabling a microgrid to run smoothly and integrate steadily. The key issues that the proposed control strategy addresses are power quality, smooth transitions between grid-connected and islanded modes, and voltage and frequency stability. This study compares the levels of self-consumption PV systems both with and without energy storage based on batteries. It also compares a baseline load profile - which does not employ load-shifting - with four other load-shifting load profiles. The simulation results demonstrate how well the proposed control system responds to grid fluctuations, shocks, and dynamic changes. The adaptability of the system to various operating scenarios is highlighted by evaluating its capacity to maintain stable operation under both normal and transient conditions. The research also investigates how the control system might improve the robustness of the Microgrid and its capacity to smoothly incorporate renewable energy sources. By providing insights into the design concepts and tactics that enable stable integration and smooth operation, the work presented advances microgrid control systems. © 2024 IEEE.

关键词： control system design Grid Integration Renewable Energy Integration Resilience Stability

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Cascade and Override Structure of SCR Process by LQR Scheme 22

Cascade and Override Structure of SCR Process by LQR Scheme

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22nd World Congress of the International Federation of Automatic control (IFAC)

作者： Kajihara, M. Shimizu, K. Akebi, T. Tani, A. Miyasaka, H. Toshiba Energy Syst & Solut Corp Yokohama Kanagawa 2300045 Japan

ISBN: (纸本)9781713872344

This paper describes the development and application of the Linear Quadratic Regulator (LQR) to the Selective Catalytic Reduction (SCR) process in a Combined Cycle (CC) Power Plant. The whole closed-loop control is implemented by the actual plant Distributed control system (DCS). To improve control dynamics, we are proposing a cascade override controller system. The effectiveness of the designed controller is evaluated by not only the simulation study but also the actual plant operation data during commercial operation. The controller covers all the operating conditions and has been continuously used from the commissioning stage to this day. Copyright (c) 2023 The Authors.

关键词： Power Plants and Power systems control system design Process control applications Advanced control Commercial application

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Multi-objective robust design approach usage in integration of bond graph and genetic programming

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INTERNATIONAL JOURNAL OF MODELLING AND SIMULATION 2022年第5期42卷 743-759页

作者： Bahrami Joo, Behzad Jamali, Ali Nariman-Zadeh, Nader Univ Guilan Fac Mech Engn Rasht Iran

In this paper, a new hybrid algorithm, based on multi-objective genetic programming and bond graphs in combination with Monte Carlo simulation, is proposed for Pareto optimal robust design of dynamical systems. For this purpose, first, an embryo model is considered for a dynamical system. Then, genetic programming is used to help this embryo model evolve through generations and achieve an optimum model. It is clear that without considering the uncertain parameters of the designing system, unwanted behaviors could occur. To overcome this, Monte Carlo simulation has been used to minimize the variations of objective functions by generating some samples around the nominal values of the uncertain parameters. In other words, the mean and variance of the objective function are minimized simultaneously through sampling, generated by Monte Carlo simulation, to reach a robust behavior. The proposed algorithm has been employed for robust design of two case studies, namely a closed-loop typewriter drive system and an optimum controller for quarter-car suspension system. A comparison between the results obtained using the proposed algorithm and those obtained through other approaches in the literature shows that more robust behavior in the presence of uncertainties can be observed in the proposed method.

关键词： control system design Multi-objective Optimization Uncertain systems system Integration Parametric Uncertainties

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Efficient Event-Based Adaptive Sliding Mode control for Spacecraft Attitude Stabilization

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JOURNAL OF GUIDANCE control AND DYNAMICS 2022年第7期45卷 1328-1336页

作者： Amrr, Syed Muhammad Chakravarty, Arghya Alam, Md Mottahir Algethami, Abdullah A. Nabi, M. Indian Inst Technol Delhi Dept Elect Engn New Delhi 110016 India Indian Inst Sci Bangalore Dept Aerosp Engn Bangalore 560012 Karnataka India King Abdulaziz Univ Dept Elect & Comp Engn Fac Engn Jeddah 21589 Saudi Arabia Taif Univ Dept Mech Engn Taif 21944 Saudi Arabia

This study investigates the problem of attitude control design for spacecraft operating in a bandwidth-restricted environment. The proposed control solution should ensure robustness toward unknown inertia and disturbance-induced uncertainties in tandem with an economically efficient utilization of network resources. The study is conducted is to develop an attitude controller that stabilizes the states of the spacecraft while avoiding unwinding problem. It also needs to provide robustness toward unknown uncertainties and disturbances with minimum use of communication resources. A comparative numerical analysis of the proposed strategy with a newly developed event triggered (ET) sliding mode control (SMC) scheme is also presented.

关键词： Sliding Mode control Attitude control system Quaternions Wireless Network Solar Radiation Satellites Input to State Stability control system design Spacecraft Dynamics Spacecraft system

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