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Digital Twin Enabled flight control system Testing: Design, Development, and Implementation

IEEE TRANSACTIONS ON AUTOMATION SCIENCE AND ENGINEERING 2025年 22卷 11318-11332页

作者： Ren, Cheng Xu, Jiaxin Chen, Cailian Zhu, Shanying Ma, Yehan Guan, Xinping Hong Kong Polytech Univ Dept Ind & Syst Engn Hong Kong Peoples R China Shanghai Jiao Tong Univ Shanghai Engn Res Ctr Intelligent Control & Manage Dept Automat Minist China Shanghai 200240 Peoples R China Shanghai Jiao Tong Univ Key Lab Syst Control & Informat Proc Minist China Shanghai 200240 Peoples R China

flight control system testing (FCST) is one of the most important process to check whether flight control surfaces can operate properly according to commands during aircraft assembly. Traditional testing method relies heavily on manual labor, leading to low efficiency and inconsistent quality. In this paper, we apply digital twin (DT) technology to the FCST process for the first time. We firstly design an architecture of DT-enabled FCST including four layers to support further development. Then, we present a triangular mesh alignment-based angle measurement (TMA-AM) algorithm to efficiently collect deflection angle data for DT-enabled FCST. Extensive experiments conducted on a aircraft wing subassembly platform show that the TMA-AM algorithm achieves an average angular measurement error of less than 0.1 degrees, outperforming existing methods. Moreover, we develop a virtual experimental platform named DT-FCST aligned with a real aircraft wing subassembly platform. In addition, TMA-AM algorithm is integrated with the DT-FCST platform. By integrating real-time data from the cockpit, real-time physical-virtual interaction of aircraft control sticks and flight control surfaces are achieved, ensuring consistency between physical and virtual movements. The integration of DT technology with the TMA-AM algorithm enables real-time synchronization, monitoring, and unified data management, significantly enhancing the efficiency and accuracy of the FCST. Note to Practitioners-To address the inefficiencies and low monitoring quality associated with traditional manual testing methods in flight control system testing (FCST), we firstly introduce digital twin (DT) technology to this process. To support effective and accurate measurement during the FCST, we propose a vision-based method tailored to accurately measure deflection angles of flight control surfaces. This method replaces manual measurements with a non-contact approach, significantly improving measurement accuracy and eff

关键词： Digital twin testing flight control system vision-based measurement physical-virtual interaction Digital twin testing flight control system vision-based measurement physical-virtual interaction

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Gradient-Based Performance Optimization for flight control system With Real-Time Data

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IEEE TRANSACTIONS ON systemS MAN CYBERNETICS-systemS 2025年第4期55卷 2537-2545页

作者： Zhao, Zhengen Xu, Yunsong Wen, Guanghui Nanjing Univ Aeronaut & Astronaut Coll Automat Engn Nanjing 211106 Peoples R China Natl Univ Def Technol Coll Intelligence Sci & Technol Changsha 410073 Peoples R China Southeast Univ Sch Math Dept Syst Sci Nanjing 211189 Peoples R China

A flight control system acts as a core subsystem in aircraft for the purpose of attitude control and trajectory tracking. Due to the inaccurate system modeling and the internal/external disturbances (e.g., wind disturbance, aerodynamic parameter change, and load perturbation), the performance of controller designed for the typical operating points may be not optimal for the full flight envelope. This article aims to address the control performance optimization problem of flight control system in the presence of an incompletely known aircraft model and real-time flight data. First, the longitudinal aircraft dynamic model is formulated, followed by the establishment of two typical disturbance models, including periodic and constant disturbances. Subsequently, a real-time optimization framework for enhancing flight control performance is introduced, with the aid of residual-driven realization of Youla parameterized controller. Moreover, the gradient-based performance optimization strategy is proposed to mitigate the performance degradation induced by disturbances, using the online monitored actuator and sensor data of flight control system. By developing tools from optimization theory, the convergence and optimality of gradient-based performance optimization method are analyzed comprehensively. Finally, the proposed methods are testified on the model of an aircraft.

关键词： Optimization Aircraft Atmospheric modeling control systems Aerospace control Real-time systems Load modeling Robustness Aerodynamics Uncertainty Data-driven flight control system gradient descent performance optimization real time

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Modeling and Mode Switching Analysis of Electro-hydrostatic Actuators for Primary flight control system

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Transactions of Nanjing University of Aeronautics and Astronautics 2025年第1期42卷 25-36页

作者： GUO Tuanhui FU Yongling CHEN Juan School of Mechanical Engineering and Automation Beihang UniversityBeijing 100191P.R.China The Laboratory of Aerospace Servo Actuation and Transmission Beijing 100191P.R.China

With the advancement of more electric aircraft(MEA)technology,the application of electro-hydrostatic actuators(EHAs)in aircraft actuation systems has become increasingly *** paper focuses on the modeling and mode switching analysis of EHA used in the primary flight control actuation systems of large aircraft,addressing the challenges associated with mode ***,we analyze the functional architecture and operational characteristics of multi-mode EHA,and sumarize the operating modes and implementation *** on the EHA system architecture,we then develop a theoretical mathematical model and a simulation *** the simulation model,we analyze the performance of the EHA during normal ***,the performance of the EHA during mode switching under various functional switching scenarios is *** results indicate that the EHA meets the performance requirements in terms of accuracy,bandwidth,and load ***,the hydraulic cylinder operates smoothly during the EHA mode switching,and the response time for switching between different modes is less than the specified *** findings validate the system performance of multi-mode EHA,which helps to improve the reliability of EHA and the safety of aircraft flight control systems.

关键词： large aircraft flight control system electro-hydrostatic actuator(EHA) mode switching simulation analysis

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flight control system design of UAV with wing incidence angle simultaneously and stochastically varied

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AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY 2024年第5期96卷 715-725页

作者： Uzun, Metin Iskenderun Tech Univ Dept Aircraft Maintenance & Repair Iskenderun Turkiye

PurposeThis study aims to simultaneously and stochastically maximize autonomous flight performance of a variable wing incidence angle having an unmanned aerial vehicle (UAV) and its flight control system (FCS) ***/methodology/approachA small UAV is produced in Iskenderun Technical University Drone Laboratory. Its wing incidence angle is able to change before UAV flight. FCS parameters and wing incidence angle are simultaneously and stochastically designed to maximize autonomous flight performance using an optimization method named simultaneous perturbation stochastic approximation. Obtained results are also benefitted during UAV flight *** simultaneous and stochastic design approach for a UAV having passively morphing wing incidence angle and its flight control system, autonomous flight performance is *** limitations/implicationsPermission of the Directorate General of Civil Aviation in Turkish Republic is necessary for real-time *** implicationsSimultaneous stochastic variable wing incidence angle having UAV and its flight control system design approach is so useful for maximizing UAV autonomous flight *** implicationsSimultaneous stochastic variable wing incidence angle having UAV and its flight control system design methodology succeeds confidence, excellent autonomous performance index and practical service interests of UAV ***/valueCreating an innovative method to recover autonomous flight performance of a UAV and generating an innovative procedure carrying out simultaneous stochastic variable wing incidence angle having UAV and its flight control system design idea.

关键词： UAVs Wing incidence Angle flight control system PID controller Simultaneous stochastic design Autonomous flight performance

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flight control system design considering rate saturation

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AEROSPACE SCIENCE AND TECHNOLOGY 1998年第4期2卷 265-275页

作者： Duda, H DLR Inst Flight Mech German Aerosp Ctr D-38022 Braunschweig Germany

In this paper the design process of modern flight control systems is discussed with respect to pilot-in-the-loop oscillations (PIO) due to rate saturation. At first the PIO phenomenon is characterised briefly. Well-known design criteria with respect to flight control system stability and handling qualities based on linear aircraft models are presented. A new design criterion considering the nonlinear effects of rate limiting is described. The criterion is based on the 'open loop onset point' (OLOP) of the rate limiter in a Nichols chart, The background for the development, and the verification of the OLOP-criterion are presented briefly. In order to demonstrate the applicability of the OLOP-criterion in the design process a simple example is examined, The flight control system parameters of a basically unstable aircraft are optimised with respect to the linear design criteria and the OLOP-criterion. Two alternative designs were discussed, a 'nominal design' and a 'low gain design' with reduced feedback loop gain. The low gain design is favourable with respect to rate limiting in the feedback loop of the flight control system, which is proved by nonlinear simulations in the time domain. Finally, the utilisation and the design of a rate limitation in the forward path of the flight control system are discussed. (C) Elsevier, Paris.

关键词： flying qualities flight control system aircraft-pilot coupling pilot-in-the-loop oscillations nonlinear system rate limiting

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flight control system failure modeling and verification based on SPIN

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ENGINEERING FAILURE ANALYSIS 2017年 82卷 501-513页

作者： Wei, Qianxin Jiao, Jian Zhao, Tingdi Beihang Univ Sch Reliabil & Syst Engn Beijing 100191 Peoples R China

In the safety-critical systems domain, model-based safety analysis is an increasingly popular approach for failure assessment and verification, which utilizes model checking to verify whether there exist failures and their combinations in system that can lead to hazards. As a formal method, model checking explores the state space of a system model automatically to verify whether it meets safety requirements. Based on a highly-process description language called Promela, SPIN is an efficient model checker that can build system model to describe system's execution and perform random or interactive simulations to identify the failures hazards in system. flight control system (FCS) is one of the safety-critical systems in aircraft. This paper proposed a method that can be used to analyze through model checking whether there are potential failures and their combinations in FCS that can lead to hazards. The system model which is described by Promela is constructed in SPIN platform based on the control logic of FCS, and the subsystems in the FCS are abstracted for processes interacting with each other. The properties to be verified are defined by Linear Temporal Logic (LTL) formulas. The potential combinations of failures in FCS can be identified by analyzing the counter-examples produced by model checking, and the accident paths that lead to the hazard of FCS can be found as well. Results of SPIN model checker show that the proposed method can be effectively used to verify and find the combinations of failures that lead to the hazard in FCS.

关键词： Failure modeling Failure verification Model checking flight control system

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flight control system design with rate saturating actuators

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JOURNAL OF GUIDANCE control AND DYNAMICS 1997年第1期20卷 90-96页

作者： Hess, RA Snell, SA University of California Davis Davis California 95616

Actuator rate saturation is an important factor adversely affecting the stability and performance of aircraft flight control systems. It has been identified as a catalyst in pilot induced oscillations, some of which have been catastrophic. A simple design technique is described that utilizes software rate limiters to improve the performance of control systems operating in the presence of actuator rate saturation. As described, the technique requires control effectors to be ganged such that any effector is driven by only a single compensated error signal. Using an analysis of the steady-state behavior of the system, requirements are placed upon the type of the loop transmissions and compensators in the proposed technique. Application of the technique to the design of a multi-input/multi output, lateral-directional control system for a simple model of a high-performance lighter is demonstrated as are the stability and performance improvements that can accrue with the technique.

关键词： Linear Actuator control system Design flight control system Pilot Induced Oscillation Catalysts Closed Loop Transfer Function Ailerons Sideslip Angle Thrust Vectoring systems Software

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flight control system of a Robotic Portable Unmanned Aerial Vehicle

Flight Control System of a Robotic Portable Unmanned Aerial ...

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2nd IEEE International Conference on Advanced Computer control

作者： Rao, Jinjun Gao, Tongyue Jiang, Zhen Gong, Zhenbang Shanghai Univ Dept Precis Mech Engn Shanghai Peoples R China

ISBN: (纸本)9781424458479

Portable fixed-wing Unmanned Aerial Vehicles (PUAV) present enormous potential. In order to develop a robotic PUAV with significant levels of autonomy, the flight control system is studied. The platform is introduced and dynamics model is studied firstly. Then the infrastructure hardware and the architecture of the flight control system are detailed. As the core of the flight control system, the attitude controller using variable fuzzy controller is investigated, and a bilinear interpolation approach is presented to realize quick inference with low computation cost of the embedded micro processor. The flight simulation and experiment validates the performance of the flight control system of PUAV.

关键词： flight control system portable unmanned aerial vehicles variable universe fuzzy control bilinear interpolation

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flight control system Design for Fixed Wing Aircraft 10

Flight Control System Design for Fixed Wing Aircraft

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10th International Conference on Recent Advances in Air and Space Technologies (RAST)

作者： Bodur, Aysenur Ucun, Levent Yildiz Tech Univ Dept Control & Automat Engn Istanbul Turkiye

ISBN: (纸本)9798350323023

The aviation sector develops cutting-edge technology and has strategic consequences all around the world. Fighter aircraft is one of the key players in air defense systems. To ensure flight safety and improve the flight capabilities of the aircraft, flight control technologies are being developed. In this study, three degrees of freedom nonlinear mathematical model of the F16 aircraft is utilized, and a flight control system operating on the longitudinal axis is designed. Trim point searching and linearization is carried out during the controller design process. The primary goal of the study is to create an autopilot system for the aircraft to follow the desired altitude and maintain a straight course by using LQR (linear quadratic regulator) and PD (proportional-derivative) controllers. The second goal of the study is to develop an autopilot system that provides control of the airspeed of the aircraft via FOPID (fractional-order proportional-integral-derivative) controller. Finally, the nonlinear model of the aircraft and the designed autopilot system are used for the simulation studies.

关键词： flight control system fixed-wing aircraft LQR FOPID

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flight control system Reliability Study Based on Hidden Markov Model Imperfect Fault Coverage Model-Hidden Markov Model

Flight Control System Reliability Study Based on Hidden Mark...

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International Conference on Quality, Reliability, Risk, Maintenance and Safety Engineering (ICQR2MSE)

作者： Li, Xiaopeng Wan, Hu Gong, Zhean Wang, Zhonglai Huang, Hong-Zhong Univ Elect Sci & Technol China Sch Mechatron Engn Chengdu 610054 Peoples R China

ISBN: (纸本)9781457712326

The reliability level of the flight control system (FCS) is one of the most important factor for air vehicle safety. Modern FCS usually use redundancy technology and built-in test (BIT) technology to improve the system reliability. However, false alarm (FA), missed alarm (MA) of BIT, the fault coverage and the system state-transition often decrease the system reliability performance. This paper studies the system imperfect fault coverage model (IFCM). This study is based on the overall consideration of the effect on the similar parallel redundancy FCS reliability, which is caused by FA and MA when measuring the fault coverage probability's effect to the system reliability. We use the Hidden Markov Model (HMM) to improve BIT measurement capability of the system status transition, and define the system real state. Compared with traditional approaches, the new model has broader applications and provides a better reference for air vehicle flight safety assessment in complex circumstances

关键词： flight control system built-in test false alarm missed alarm imperfect fault coverage model hidden markov model

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