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检索条件"主题词=Flight Control System"

共 721 条记录，以下是81-90 订阅

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Design and simulation of large envelope flight control system

Design and simulation of large envelope flight control syste...

引用

Asia Simulation Conference/6th International Conference on system Simulation and Scientific Computing

作者： Zhang, DF Gao, JY Beihang Univ Dept Automat Control Beijing 100083 Peoples R China

ISBN: (纸本)7506278413

Modem robust self-scheduling technique is applied to design the flight control system for an unmanned aerial vehicle (UAV) which has a large operating range. The fast modes of scheduling controller are limited based on the disk theorem for the sake of digital implement. Firstly the UAV is approximate to an affine linear parameter varying plant using least square method. Then the robust controller is obtained, and its gain is scheduled with dynamic pressure and altitude. The structure of envelope flight control system is proposed. And the flight simulation including almost all flight modes is made with 6-freedom nonlinear model of the UAV. The result shows that the designed flight control system has satisfactory global robust stability and robust performance.

关键词： robust control flight control system envelope flight simulation UAV

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Implementation of system Identification and flight control system for UAV 3

Implementation of System Identification and Flight Control S...

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3rd IEEE International Conference on control, Automation and Robotics (ICCAR)

作者： Saengphet, Watcharapol Tantrairatn, Suradet Thumtae, Chalothorn Srisertpol, Jiraphon Suranaree Univ Technol Sch Mech Engn Nakhon Ratchasima Thailand

ISBN: (纸本)9781509060887

This paper presents a methodology to implement a flight control system based on PID control design for PX4 autopilot system. The objective of the method is to find out the optimal controller gains on the same control structure of PX4 flight stack software without iterative controller tuning. This is achieved through a two-step procedure which consist of aircraft system identification and PID optimized control design. The first step to implement an autopilot system on an Unmanned Aerial Vehicle (UAV) relates to characterizing the UAV's dynamics using a mathematical model. To accomplish the accuracy of the particular UAV control, the process of system identification, which is the estimation of the parameters of the equation of motion, is essential. The measurement of inputs and outputs during manual flight is utilized to determine the unknown parameters of SISO mathematical model using a software of comprehensive identification from frequency responses. Subsequently, the model is utilized for an optimization-based tuning of these PID controller gains offline in order to minimize the requirement of numerous in-flight tuning. The controller is implemented on PX4 autopilot system. The results are demonstrated that the tracking control system has excellent dynamic performance in respect of simple design, high precision, and easy implement.

关键词： flight control system UAV control system identification

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A Review of Electric Actuation and flight control system for More/All Electric Aircraft 24

A Review of Electric Actuation and Flight Control System for...

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24th International Conference on Electrical Machines and systems (ICEMS)

作者： Bae, Junhyung Daegu Catholic Univ Sch Elect & Elect Engn Gyongsan Gyeongbuk South Korea

ISBN: (纸本)9788986510218

In recent decades, the aviation industry has made remarkable progress based on the development of different types of aircraft. Recent aircraft have begun to employ a large number of electrically powered equipment, as in the case of electric vehicles. These aircraft are referred to as M/AEA (More/All Electric Aircraft), and for civil aircraft, Boeing 787 and Airbus 380, began to apply these technologies significantly. Current aircrafts are being replaced by electrically powered equipment without the use of engine bleed air, which is the main source of secondary power, hydraulic systems and pneumatic pressure. This not only simplifies aircraft design and reduces weight, but also improves engine efficiency, making it an eco-friendly aircraft that improves fuel consumption and reduces pollutant emissions. In this paper, the author gave an overview and review electrically driven subsystems and flight control systems for M/AEA.

关键词： M/AEA Electric Actuator Electric Brake system Electric Generator flight control system

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Research on Modeling Method of Aeronautical Weapon flight control system Based on Harmony-SE 16

Research on Modeling Method of Aeronautical Weapon Flight Co...

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16th IEEE Conference on Industrial Electronics and Applications (ICIEA)

作者： Li, Xiatong Hu, Xiaoguang Xiao, Jin Zhang, Guofeng Liu, Lei Beihang Univ State Key Lab Virtual Real Technol & Syst Beijing Peoples R China Beijing Electromech Inst Beijing Peoples R China

ISBN: (纸本)9781665422482

This paper establishes the flight control system model using the Harmony-SE method, and realizes simulation of the aeronautical weapon trajectory from the launching point to the target point. The characteristic of flight control system of aeronautical weapon is that all functions revolved around the calculation and iteration of system state. Since the main idea of Harmony-SE is to design the system architecture and system function based on use cases, there are redundant steps such as analyzing the context of use cases in the process of modeling the system with this characteristic, which is inefficient. To solve this problem, this paper puts forward an optimization method. On the basis of Harmony-SE, this paper optimizes the architecture analysis and design method based on the function flow in the Harmony-SE method, simplifies the system model architecture, proposes the architecture design method based on the information flow, which simplifies Harmony-SE steps by using the information flow to suture function flow, thus improve the modeling efficiency of the flight control system.

关键词： Harmony-SE flight control system modeling and simulation information flow

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Design of Missile flight control system Based on Variable Structure control Theory 36

Design of Missile Flight Control System Based on Variable St...

引用

第36届中国控制会议

作者： Jiang Lou Zhihao Cai Jiang Zhao Kun Wu Yingxun Wang School of Automation Science and Electrical Engineering Beihang University

ISBN: (纸本)9781538629185

flight control system plays an important role in the process of missile *** quality of flight control system will affect the missile’s performance *** this article,we design a flight control system using variable structure control ***,we establish a mathematical model of the missile and the basic content of variable structure control theory is *** chapter are mainly aiming at designing the control system of the missile’s normal ***,the linearized missile’s normal overload is designed by using the mathematical model in chapter *** the variable structure controller is *** addition,we use the variable structure controller to optimize the linear normal load control *** numerical simulation of two different control methods are *** the result illustrate that the robustness of the control system based on variable structure theory are better.

关键词： flight control system linearization control variable structure control

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A Reconfigurable flight control system Architecture for Small Unmanned Aerial Vehicles

A Reconfigurable Flight Control System Architecture for Smal...

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6th IEEE International systems Conference (SYS CON)

作者： Deng, Zhicheng Ma, Chuanbao Zhu, Ming Beihang Univ Sch Aeronaut Sci & Engn Beijing Peoples R China

ISBN: (纸本)9781467307499

Small Unmanned Aerial Vehicles (UAVs) have been proposed for use in a variety of areas including hazard analysis, disaster monitoring, agricultural mapping, and so on. Currently, the development of flight control systems (FCS) for small UAVs is complicated, time-consuming and error-prone. To address these challenges, we present a reconfigurable flight control system architecture (RFCSA) for small UAVs. RFCSA allows rapidly integrating hardware modules and verifying control laws. It utilizes a modular-based framework, in which implementation details of a typical function are packaged into a function module. In addition, each function module in RFCSA is stand-alone with its own processors, memories, power conversion and communication interfaces. In this way, the system designer could be able to focus on the system implementation, rather than pay much attention to the design details of low-level functions. Moreover, an event-driven Service-Oriented Architectures (SOA) is proposed to minimize the coupling between modules and improve the performance of inter-module interactions. The paper is organized as follows: Firstly, the challenges and requirements for small UAVs' flight control systems are discussed. Secondly, the hardware architecture based on modular concept is developed. Thirdly, event driven SOA is proposed, and the mechanisms for modules to share information and coordinate activities are introduced. Finally, the conclusion and future work is pointed out.

关键词： flight control system unmanned aerial vehicles service oriented architecture

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Simultaneous Computation of the Speed and Fuel Parameters of flight control system by using Anfis and Artificial Neural Networks 24

Simultaneous Computation of the Speed and Fuel Parameters of...

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24th Signal Processing and Communication Application Conference (SIU)

作者： Konar, Mehmet Bagis, Aytekin Erciyes Univ Ucak Elekt Elekt Bolumu Kayseri Turkey Erciyes Univ Elekt Elekt Muhendisligi Bolumu Kayseri Turkey

ISBN: (纸本)9781509016792

As a natural result of the growing air transportation, the importance of the fligth control systems that simultaneously evaluates the many parameters has increased greatly. This study presents the results of a modeling examination based on the use of Anfis and artificial neural networks for simultaneously determination of speed and fuel parameters of the flight control system. In the study given for Boeing B-767-200 type planes, model structures have three inputs y, a, r which are altitude, weigth, and engine pressure ratio, and two outputs h, f which specifies flying speed and fuel amount, respectively. The results obtained from the models are presented in comparison with the actual values.

关键词： artificial neural networks ANFIS system modeling flight control system

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Robust longitudinal flight control system under weight and center of gravity uncertainty

Robust longitudinal flight control system under weight and c...

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15th IEEE Canadian Conference on Electrical and Computer Engineering

作者： Hentabli, K Akhrif, O Saydy, L Ecole Technol Super Dept Elect Engn Montreal PQ H3C 1K3 Canada

ISBN: (纸本)0780377818

This paper presents a post-design robustness assessment for flight control systems that have been designed using two different techniques, namely H,, and p.-synthesis, for the longitudinal pitch rate control system of the Bom-badrier Challenger 604. In order to perform the analysis of flight control systems, a linear fractional representation (LFT) of the aircraft model is generated. We consider the longitudinal linear equations of motion (both short-period and phugoid modes of the aircraft). The LFT model presents uncertainty in the aerodynamic parameters due to aircraft mass and center of gravity variations. The closed-loop system combined with each controller is used to determine stability robustness and performance robustness with respect to changes in aerodynamic parameters. We also determine the corresponding stability margins and the worst-case parameter combinations destabilizing the system. The objective is to verify that the control system remains stable and achieves desired performance with predicted Level 1 handling qualities for all possible parameter variations over a specified range. Simulation results are given to validate our approach.

关键词： flight control system linear fractional transformation performance and robustness stability worst-case perturbation structured singular value

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Compound Faults Parameter Estimation and Fault-tolerant control in F-16 Fighter flight control system 2

Compound Faults Parameter Estimation and Fault-tolerant Cont...

引用

2nd Conference on Fully Actuated system Theory and Applications (CFASTA)

作者： Yu, Shuaixian Jin, Fan Zhou, Yiwen Li, Yuqing Wei, Qizhao Shanghai Aerosp Control Technol Inst Shanghai 201100 Peoples R China

ISBN: (纸本)9798350332162

Aims at the compound faults of the flight control system of F-16 fighter, which is composed of pitch rate sensor and aileron fault, this paper proposes a dual-channel state estimation scheme to estimate multiple fault parameters based on the observer principle at the same time. According to the fault estimation results, the flight control system can be fault-toleranted. The three-channel state coupling characteristic of pitch and yaw roll makes the control system introduce other fault information when detecting and diagnosing a single fault, which seriously reduces the accuracy of fault diagnosis. In this paper, hy constructing two observers in different channels and designing the estimated parameter change rate in the observer based on Lyapunov stability theory, the residual error of the two observers can converge synchronously. Then the fault parameters can be estimated in the observer system. Based on the nonlinear dynamic inverse control scheme and the compensated state quantity, the flight control performance of the fighter can be improved.

关键词： flight control system Dual-channel observer Compound faults Fault diagnosis Fault-tolerant control

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Research on Fault Diagnosis Technology of UAV flight control system Based on Hybrid Diagnosis Engine

Research on Fault Diagnosis Technology of UAV Flight Control...

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Prognostics and Health Management Conference (PHM-2022 London)

作者： Chen, Mingjie Yan, Jin Li, Tieying Chi, Chengzhi China Aeronaut Radio Elect Res Inst Key Lab Sci & Technol Av Integrat Technol Shanghai Peoples R China

ISBN: (纸本)9781665479547

In order to solve the problem of real-time fault diagnosis of UAV flight control system, a fault diagnosis method based on hybrid diagnosis engine is proposed. Aiming at the multiple fault modes and cross-linking relationships of each node in the flight control system, the system reference model is established by qualitative and quantitative methods, and then a corresponding domain model is established according to the flight control system of a specific model. Finally, the fault diagnosis reasoning engine based on the model and the hybrid diagnosis engine realizes the diagnosis of the current fault of the system. The results show that this method can determine the time and location of the fault in real time and accurately, which provides an effective guarantee for improving the efficiency of UAV fault diagnosis and improving the flight safety of UAV.

关键词： UAV flight control system reference model domain model fault diagnosis

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