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

作者： Gäßler, Björn Robens, Johannes German Aerospace Center Institute for System Dynamics and Control Space Systems Department DLR German Aerospace Center Institute of System Dynamics and Control OberpfaffenhofenD-82234 Germany

ISBN: (数字)9781624107238

ISBN: (纸本)9781624107238

The Reusability Flight Experiment (ReFEx) is a technology demonstrator developed by the German Aerospace Center (DLR) for a launch vehicle with vertical takeoff and horizontal landing capabilities. Its objective is to verify key technologies critical to the reusability of a launch vehicle’s first stage and boosters. During atmospheric flight, the vehicle’s trajectory spans a wide range of Mach numbers and angles of attack. The vehicle encounters substantial shifts in dynamic pressure and highly nonlinear aerodynamic effects. These include sign changes in the control derivatives and singularities, where the lateral motion may become uncontrollable. The aerodynamic control surfaces, which are applied to control the vehicle’s attitude, exhibit strong cross-coupling and varying effectiveness. Given the uncertainties in the vehicle’s mechanical properties and aerodynamic data, a reliable control design capable of handling the uncertainties and disturbances is essential. The flight controller presented in this paper addresses these challenges by combining a cascaded control architecture based on nonlinear dynamic inversion (NDI) with an incremental NDI approach for control allocation. For fast guidance reference signal tracking the presented controller employs feed-forward control while uncertainties, disturbances and model mismatches are compensated by linear feedback controllers. A control allocation based on a damped-least squares optimization approach determines aerodynamic control surface deflections and prevents excessive control actions in the vicinity of singularities. Simulation results and Monte Carlo campaigns validate the selected control approach and demonstrate that the proposed flight controller is capable of tracking the trajectory in the presence of disturbances and uncertainties. © 2025, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： Angle of attack

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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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Aeroservoelastic induced drag modelling and minimization for the T-FLEX demonstrator

Aeroservoelastic induced drag modelling and minimization for...

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AIAA SciTech Forum and Exposition, 2023

作者： Meddaikar, Yasser M. Krüger, Wolf R. Kier, Thiemo Bartasevicius, Julius Yu, Fanglin Vanek, Bálint Olgyay, Ábel Takarics, Béla Loads Analysis and Aeroelastic Design DLR - Institute of Aeroelasticity Bunsenstrasse 10 Goettingen37073 Germany Department of System Dynamics and Control DLR - Institute of System Dynamics and Control Weßling82234 Germany Institute of Aircraft Design Technical University of Munich Boltzmannstraße 15 Garching/München85748 Germany Systems and Control Lab SZTAKI Kende u. 13-17 Budapest1111 Hungary Computer and Automation Research Institute SZTAKI Kendeu. 13-17 Budapest1111 Hungary

ISBN: (数字)9781624106996

ISBN: (纸本)9781624106996

This work is part of the on-going EU-project FliPASED, wherein flight tests using a UAV demonstrator (T-FLEX) and a multi-disciplinary optimization (MDO) exercise involving the aeroservoelastic optimization of UAV demonstrator and commercial-scale aircraft wings are performed. In this paper, several potential flow methods have been applied to estimate induced drag of the T-FLEX aircraft, followed by solving an optimization problem to minimize it using the control surfaces on the wings. The results from this study were used in the retrofit design of a pair of manufactured wings - the number and position of the control surfaces and the wing selection. In a next step, the developed tools will form the basis for a controller that will minimize induced drag, which will be tested on the T-FLEX testbed. The developed tools and the validated results will also be used within a broader MDO task involving optimization studies on a commercial short/medium range aircraft. © 2023, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： Wings

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SWITCHING ACTIVITY IN AN ENSEMBLE OF EXCITABLE NEURONS

arXiv

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arXiv 2023年

作者： Korotkov, A.G. Zagrebin, S.Y. Osipov, G.V. Department of Control Theory and System Dynamics Scientific and Educational Mathematical Center "Mathematics of future technologies"

The paper proposes two dynamical systems based on the generalized Lotka-Volterra model of three excitable elements interacting through excitatory couplings. It is shown that for some values of the coupling parameters in the phase space of systems, there are heteroclinic cycles containing three or six saddle equilibrium states and heteroclinic curves connecting them. Under certain external stimuli that transfer the system from a stable zero equilibrium state to a small neighborhood of the heteroclinic cycle, the phase trajectory will alternately visit the neighborhood of saddle equilibrium states (possibly more than once), after which it will return to its initial state. The described behavior is proposed to be used to simulate switching activity in neural ensembles. Different transients are determined by different external stimuli. The passage of the phase point of the system near the saddle equilibrium states included in the heteroclinic circuit is proposed to be interpreted as activation of the corresponding element. © 2023, CC BY.

关键词： Dynamical systems

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Parallel Clustering Algorithm for the k-medoids Problem in High-dimensional Space for Large-scale Datasets 19

Parallel Clustering Algorithm for the k-medoids Problem in H...

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19th International Asian School-Seminar on Optimization Problems of Complex systems, OPCS 2023

作者： Vandanov, Sergey Plyasunov, Aleksandr Ushakov, Anton Novosibirsk State University Department of Physics Novosibirsk Russia Sobolev Institute of Mathematics of Sb Ras Lab. of Mathematical Models of Decision Making Novosibirsk Russia Matrosov Institute for System Dynamics and Control Theory of Sb Ras Irkutsk Russia

ISBN: (纸本)9798350331134

We present a robust, parallel primal-dual heuristic algorithm for the k-medoids clustering problem, a widely utilized method in data mining and machine learning. Our approach surpasses current algorithms by effectively addressing their limitations, such as time-consuming distance matrix calculations, inefficient nearest-neighbor searches, and difficulties in handling large-scale datasets. To overcome these challenges, we employ an efficient parallel implementation, combined with a pioneering subgradient search algorithm. We evaluate our algorithm on the BIRCH and Stanford Dog datasets and demonstrate its superiority over existing k-medoids clustering algorithms in terms of solution quality and run time. Additionally, we introduce a novel vectorization technique that enables our algorithm to handle various types of data, such as images, text, and point data. Overall, our work contributes to the field of data mining and machine learning by providing an efficient and effective solution for the k-medoids clustering problem. The proposed algorithm offers improved performance, and versatility, making it a valuable tool for a wide range of applications. © 2023 IEEE.

关键词： Clustering algorithms

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Block-oriented non-linear identification of a dynamical equilibrium: Application to a supercritical Hopf bifurcation model

Block-oriented non-linear identification of a dynamical equi...

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European control Conference (ECC)

作者： Fabrice Demourant Beatrice Jacquier Alexandre Janot System Control and Flight Dynamics Department 2 avenue Edouard Belin BP74025 Research scientists Toulouse France

The article deals with the non-linear identification using a block structure to reproduce the behavior of a unknown non-linear system which presents two equilibria: a static equilibrium point, which is in our case unstable, and a dynamic equilibrium, which can correspond, for example, to a Limit Cycle Oscillation (LCO). This non-linear system is representative of a supercritical model which appears in the Hopf bifurcation. The generic proposed methodology is based on three identification steps: firstly the linear identification of the static equilibrium, called the fixed point, secondly, the identification of a Wiener feedback structure to reproduce the LCO, and lastly the tuning of a Wiener-Hammerstein feedback structure to improve the accuracy level of the identified nonlinear model. Finally, time-domain simulations are performed to evaluate and compare results with the original non-linear system.

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Deep Neural Network Based Optimal control of Greenhouses

Deep Neural Network Based Optimal Control of Greenhouses

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European control Conference (ECC)

作者： Kiran Kumar Sathyanarayanan Philipp Sauerteig Stefan Streif Automatic Control and System Dynamics Lab Technische Universität Chemnitz Chemnitz Germany Department of Bioresources Fraunhofer Institute for Molecular Biology and Applied Ecology Giessen Germany

ISBN: (数字)9783907144107

ISBN: (纸本)9798331540920

Automatic control of greenhouse crop production is of great interest owing to the increasing energy and labor costs. In this work, we use two-level control, where the upper level generates suitable reference trajectories for states and control inputs based on day-ahead predictions. These references are tracked in the lower level using Nonlinear Model Predictive control (NMPC). In order to apply NMPC, a model of the greenhouse dynamics is essential. However, the complex nature of the underlying model including discontinuities and nonlinearities results in intractable computational complexity and long sampling times. As a remedy, we employ NMPC as a data generator to learn the tracking control policy using deep neural networks. Then, the references are tracked using the trained Deep Neural Network (DNN) to reduce the computational burden. The efficiency of our approach under real-time disturbances is demonstrated by means of a simulation study.

关键词： Power demand Computational modeling Memory management Optimal control Artificial neural networks Production Real-time systems

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Nodes2STRNet for structural dense displacement recognition by deformable mesh model and motion representation

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International Journal of Mechanical system dynamics 2023年第3期3卷 229-250页

作者： Jin Zhao Hui Li Yang Xu Key Lab of Smart Prevention and Mitigation of Civil Engineering Disasters of the Ministry of Industry and Information Technology Harbin Institute of TechnologyHarbinChina Key Lab of Structures Dynamics Behavior and Control of the Ministry of Education Harbin Institute of TechnologyHarbinChina School of Civil Engineering Harbin Institute of TechnologyHarbinChina Department of System Design and Simulation Goldwind Science and Technology Co.Ltd.BeijingChina

Displacement is a critical indicator for mechanical systems and civil *** vision-based displacement recognition methods mainly focus on the sparse identification of limited measurement points,and the motion representation of an entire structure is very *** study proposes a novel Nodes2STRNet for structural dense displacement recognition using a handful of structural control nodes based on a deformable structural three-dimensional mesh model,which consists of control node estimation subnetwork(NodesEstimate)and pose parameter recognition subnetwork(Nodes2PoseNet).NodesEstimate calculates the dense optical flow field based on FlowNet 2.0 and generates structural control node ***2PoseNet uses structural control node coordinates as input and regresses structural pose parameters by a multilayer perceptron.A self-supervised learning strategy is designed with a mean square error loss and L2 regularization to train *** effectiveness and accuracy of dense displacement recognition and robustness to light condition variations are validated by seismic shaking table tests of a four-story-building *** studies with image-segmentation-based Structure-PoseNet show that the proposed Nodes2STRNet can achieve higher accuracy and better robustness against light condition *** addition,NodesEstimate does not require retraining when faced with new scenarios,and Nodes2PoseNet has high self-supervised training efficiency with only a few control nodes instead of fully supervised pixel-level segmentation.

关键词： structural dense displacement recognition deformable structural mesh model deep-learning-based monocular vision self-supervised learning

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Design and Evaluation of Nonlinear Inversion Based Automated Landing control for an Airliner in a High Crosswind Scenario

Design and Evaluation of Nonlinear Inversion Based Automated...

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

作者： Kim, Ho Joong Lombaerts, Thomas Looye, Gertjan Department of Aerospace Engineering San José State University Santa Clara County San JoseCA95121 United States Aerospace Engineering Department Charles W. Davidson College of Engineering United States KBR NASA Ames Research Center Intelligent Systems Division Mail Stop 269-1 Moffett FieldCA94083 United States Institute of System Dynamics and Control German Aerospace Center DLR Weßling82234 Germany

ISBN: (数字)9781624107238

ISBN: (纸本)9781624107238

This paper describes the design and evaluation of an autoflight controller under maximized crosswind landing scenarios using Nonlinear Dynamic Inversion (NDI) and Incremental Nonlinear Dynamic Inversion (INDI) control methods. The simulation model is representative of a nonlinear, 6 DOF twin-engined civilian transport aircraft in landing configuration starting 300 meters above the runway. The designed flight controller is of cascaded control structure based upon the time scale separation principle. While only INDI based design is evaluated, each control loop implements both NDI and INDI based design, accompanied with feed forward path control for select loops. The controller is evaluated through multiple Monte Carlo statistical analyses, each set containing 2000 landings, which are performed under widely distributed environmental and system parameters. The designed INDI method based controller as discussed in this paper satisfies all safe landing criteria for crosswind landings of up to 30 knots. © 2025, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： Aircraft landing

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Dynamic modeling and analysis of the looped space tether transportation system based on ANCF

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International Journal of Mechanical system dynamics 2022年第2期2卷 204-213页

作者： Jie Yang Qingtao Wang Zhiyong Zhang Zhendong Liu Shidong Xu Gangqiang Li School of Science Nanjing University of Science and TechnologyNanjingChina Institute of Launch Dynamics Nanjing University of Science and TechnologyNanjingChina Shanghai Aerospace System Engineering Institute ShanghaiChina State Key Laboratory of Mechanics and Control of Mechanical Structures Nanjing University of Aeronautics and AstronauticsNanjingChina Department of Mechanical Engineering York UniversityTorontoCanada

A high‐fidelity multibody‐system dynamic model of the looped tether transportation system(L‐TTS)is proposed in this study to study its large deformation as well as large overall *** absolute nodal coordinate formulation(ANCF)‐based gradient‐deficient beam element is employed to establish the accurate model of the two flexible tethers subject to large *** relative movement of climbers along tethers is described by using the sliding joint model based on *** reduce the collision risks between tethers and climbers,two libration suppression strategies,namely,the decelerated motion of climbers relative to tethers and multiple climbers per tether are investigated in this *** numerical simulations not only validate the effectiveness of the two strategies in reducing the collision risks between climbers and tethers,the overall librations of L‐TTS,and the magnitudes of the longitudinal elastic force of tethers,but also verify the good performance of the high‐fidelity model proposed in this study for dynamic simulation of the L‐TTS in microgravity conditions.

关键词： looped tether transportation system high‐fidelity model absolute nodal coordinate formulation sliding joints libration suppression

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