scholarly journals Aerodynamic-Parameter Identification and Attitude Control of Quad-Rotor Model with CIFER and Adaptive LADRC

2021 ◽  
Vol 34 (1) ◽  
Author(s):  
Sen Yang ◽  
Leiping Xi ◽  
Jiaxing Hao ◽  
Wenjie Wang
Keyword(s):  
Parameter Identification ◽  
Attitude Control ◽  
Physical Simulation ◽  
Control Method ◽  
Controller Design ◽  
Estimation Method ◽  
Practical Significance ◽  
Aerodynamic Parameter ◽  
Allocation Model ◽  
The Moment

AbstractCurrent research on quadrotor modeling mainly focuses on theoretical analysis methods and experimental methods, which have problems such as weak adaptability to the environment, high test costs, and long durations. Additionally, the PID controller, which is currently widely used in quadrotors, requires improvement in anti-interference. Therefore, the aforementioned research has considerable practical significance for the modeling and controller design of quadrotors with strong coupling and nonlinear characteristics. In the present research, an aerodynamic-parameter estimation method and an adaptive attitude control method based on the linear active disturbance rejection controller (LADRC) are designed separately. First, the motion model, dynamics model, and control allocation model of the quad-rotor are established according to the aerodynamic theory and Newton–Euler equations. Next, a more accurate attitude model of the quad-rotor is obtained by using a tool called CIFER to identify the aerodynamic parameters with large uncertainties in the frequency domain. Then, an adaptive attitude decoupling controller based on the LADRC is designed to solve the problem of the poor anti-interference ability of the quad-rotor and adjust the key control parameter b0 automatically according to the change in the moment of inertia in real time. Finally, the proposed approach is verified on a semi-physical simulation platform, and it increases the tracking speed and accuracy of the controller, as well as the anti-disturbance performance and robustness of the control system. This paper proposes an effective aerodynamic-parameter identification method using CIFER and an adaptive attitude decoupling controller with a sufficient anti-interference ability.

scholarly journals Aerodynamic Parameters Identification and Adaptive LADRC Attitude Control of Quad-Rotor Model

2018 ◽  
Author(s):  
Sen Yang ◽  
Leiping Xi ◽  
Jiaxing Hao ◽  
Yuefei Zhao ◽  
Ye Yang ◽  
...  
Keyword(s):  
Attitude Control ◽  
Physical Simulation ◽  
Control Method ◽  
Estimation Method ◽  
Distribution Model ◽  
Model Parameters ◽  
Aerodynamic Parameter ◽  
External Interference ◽  
Aerodynamic Parameters ◽  
Rotor Model

In accordance with problems such as difficulty in obtaining aerodynamic parameters of a quad-rotor model, the change of model parameters with external interference affects the control performances, an aerodynamic parameter estimation method and an adaptive attitude control method based on LADRC are designed. Firstly, the motion model, dynamics model and control distribution model of quad-rotor are established by using the aerodynamic and Newtonian Euler equations. Secondly, the identification tool CIFER is used to identify the aerodynamic parameters with large uncertainties in frequency domain and a more accurate attitude model of the quad-rotor is obtained. Then an adaptive attitude decoupling controller based on LADRC is designed to solve the problem of poor anti-interference ability of the quad-rotor, so that the control parameter b0 can be automatically adjusted to identify the change of the moment of inertia in real time. Finally, a semi-physical simulation platform is used for simulation verification. The results show that the adaptive LADRC attitude controller designed can effectively estimate and compensate the system's internal and external disturbances, and the tracking speed of the controller is faster and the precision is higher which can effectively improve system's anti-interference and robustness.

Velocity-free distributed geometric formation control for underactuated UAVs

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Yanjie Chen ◽  
Weiwei Zhan ◽  
Yibin Huang ◽  
Zhiqiang Miao ◽  
Yaonan Wang
Keyword(s):  
Attitude Control ◽  
Formation Control ◽  
Control Method ◽  
Controller Design ◽  
Linear Velocity ◽  
Nonlinear Controller ◽  
Content Type ◽  
Distributed Controller ◽  
Cascade Structure ◽  
The Stability

Purpose This paper aims to investigate the distributed formation control problem for a multi-quadrotor unmanned aerial vehicle system without linear velocity feedbacks. Design/methodology/approach A nonlinear controller is proposed based on the orthogonal group SE(3) to obviate singularities and ambiguities of the traditional parameterized attitude representations. A cascade structure is applied in the distributed controller design. The inner loop is responsible for attitude control, and the outer loop is responsible for translational dynamics. To ensure a linear-velocity-free characteristic, some auxiliary variables are introduced to construct virtual signals in distributed controller design. The stability analysis of the proposed distributed control method by the Lyapunov function is provided as well. Findings A group of four quadrotors with constant reference linear velocity and a group of six quadrotors with varying reference linear velocity are adopted to verify the effectiveness of the proposed strategy. Originality/value This is a new innovation for multi-robot formation control method to improve assembly automation.

scholarly journals Adaptive Digital Disturbance Rejection Controller Design for Underwater Thermal Vehicles

2021 ◽  
Vol 9 (4) ◽  
pp. 406
Author(s):  
Guohui Wang ◽  
Yanan Yang ◽  
Shuxin Wang
Keyword(s):  
Disturbance Rejection ◽  
Control Method ◽  
Controller Design ◽  
Least Squares Method ◽  
Vertical Plane ◽  
Estimation Method ◽  
Plane Motion ◽  
External Disturbances ◽  
Control Approach ◽  
Waves And Currents

Underwater thermal vehicles, as ocean observation tools, are frequently affected by environment disturbances such as waves and currents, which may cause degradation of the observation accuracy of the vehicles. Consequently, it is important to design a controller for a vehicle that can resist ocean disturbance. In this study, an underwater thermal vehicle principle is introduced, and the mathematical model is established in the vertical plane motion. On this basis, an adaptive digital disturbance suppression control method is proposed. For known disturbance parameters, this controller could compensate for external disturbances by pre-setting control parameters using the internal model principle and parameterizations method. For the case where the disturbance parameters are unknown, disturbance parameter estimation method based on forgetting factor least-squares method is proposed to transform the unknown parameter disturbance into a disturbance with known parameters, which is then suppressed by the adaptive digital disturbance rejection control approach. This solution could effectively solve the challenges caused by parameter uncertainty and unknown time-varying ocean external disturbances. Finally, simulations are carried out for the Petrel underwater thermal glider as an example. The simulation results show the proposed control method’s superiority and inherent robustness.

scholarly journals Design of Satellite Attitude Control Algorithm Based on the SDRE Method Using Gas Jets and Reaction Wheels

2013 ◽  
Vol 2013 ◽  
pp. 1-8 ◽  
Author(s):  
Luiz C. G. de Souza ◽  
Victor M. R. Arena
Keyword(s):  
Attitude Control ◽  
Control Algorithm ◽  
Controller Design ◽  
Algorithm Design ◽  
Large Angle ◽  
Space Mission ◽  
Control Technique ◽  
Gas Jets ◽  
State Dependent ◽  
Highly Nonlinear

An experimental attitude control algorithm design using prototypes can minimize space mission costs by reducing the number of errors transmitted to the next phase of the project. The Space Mechanics and Control Division (DMC) of INPE is constructing a 3D simulator to supply the conditions for implementing and testing satellite control hardware and software. Satellite large angle maneuver makes the plant highly nonlinear and if the parameters of the system are not well determined, the plant can also present some level of uncertainty. As a result, controller designed by a linear control technique can have its performance and robustness degraded. In this paper the standard LQR linear controller and the SDRE controller associated with an SDRE filter are applied to design a controller for a nonlinear plant. The plant is similar to the DMC 3D satellite simulator where the unstructured uncertainties of the system are represented by process and measurements noise. In the sequel the State-Dependent Riccati Equation (SDRE) method is used to design and test an attitude control algorithm based on gas jets and reaction wheel torques to perform large angle maneuver in three axes. The SDRE controller design takes into account the effects of the plant nonlinearities and system noise which represents uncertainty. The SDRE controller performance and robustness are tested during the transition phase from angular velocity reductions to normal mode of operation with stringent pointing accuracy using a switching control algorithm based on minimum system energy. This work serves to validate the numerical simulator model and to verify the functionality of the control algorithm designed by the SDRE method.

scholarly journals Design and validation of an MPC controller for CMG-based testbed

2021 ◽  
Author(s):  
Matteo Facchino ◽  
Atsushi Totsuka ◽  
Elisa Capello ◽  
Satoshi Satoh ◽  
Giorgio Guglieri ◽  
...  
Keyword(s):  
Predictive Control ◽  
Attitude Control ◽  
High Speed ◽  
Control Method ◽  
Input Constraints ◽  
Virtual Reference ◽  
Control Moment ◽  
Pyramidal Configuration ◽  
Actuation Systems ◽  
Constraints Satisfaction

AbstractIn the last years, Control Moment Gyros (CMGs) are widely used for high-speed attitude control, since they are able to generate larger torque compared to “classical” actuation systems, such as Reaction Wheels . This paper describes the attitude control problem of a spacecraft, using a Model Predictive Control method. The features of the considered linear MPC are: (i) a virtual reference, to guarantee input constraints satisfaction, and (ii) an integrator state as a servo compensator, to reduce the steady-state error. Moreover, the real-time implementability is investigated using an experimental testbed with four CMGs in pyramidal configuration, where the capability of attitude control and the optimization solver for embedded systems are focused on. The effectiveness and the performance of the control system are shown in both simulations and experiments.

Design of Semi-Physical Simulation for Small Satellite by Virtual Display

2011 ◽  
Vol 130-134 ◽  
pp. 2684-2687 ◽  
Author(s):  
Kai Xu ◽  
Yan Lv ◽  
Guang Jin
Keyword(s):  
Control System ◽  
Real Time ◽  
Attitude Control ◽  
Physical Simulation ◽  
Simulation System ◽  
Space Environment ◽  
Small Satellite ◽  
Attitude Control System ◽  
Actual Environment ◽  
Virtual Display

Semi-physical simulation of attitude control system is the more synthetically test and verify for designing of small satellite control system. It is an important means of small satellite development. However, the results of current semi-physical simulation system have a lot of non-intuitive. Compare with the actual environment, the simulation environment still has striking disparity. So the shortcomings affect precision of simulation. Based on the virtual display technology, the group semi-physical simulation system has been constructed for attitude control of small satellite due to the combination with xPC real-time environment, the simulation computer, high-precision single-axis air-bearing turntable, reaction wheel, air thrust device, fiber gyroscopes, sensors synchronizer, power subsystem and wireless devices virtual display computer etc. Semi-physical simulation achieved the visual simulation in orbit and tracked new information of virtual environment of space into real-time simulation computer. Simulation results show that the simulation system for real-time attitude and orbit position of small satellite semi-physical simulation has an excellent display effect. At the same time, Real-time transfuse of orbit information provides a more accurate space environment simulation. The simulation system of small satellite attitude control to design and evaluate the more direct and convenient.

scholarly journals Sinusoidal Control of a Brushless DC Motor with Misalignment of Hall Sensors

Energies ◽  
2021 ◽  
Vol 14 (13) ◽  
pp. 3845
Author(s):  
Krzysztof Kolano ◽  
Bartosz Drzymała ◽  
Jakub Gęca
Keyword(s):  
Control Method ◽  
Acoustic Noise ◽  
Negative Impact ◽  
Estimation Method ◽  
Large Error ◽  
Position Estimation ◽  
Actual System ◽  
Brushless Dc ◽  
Hall Sensors ◽  
Torque Ripples

This article presents an estimation method of the BLDC rotor position with asymmetrically arranged Hall sensors. Position estimation is necessary to control the motor by methods other than block commutation. A sinusoidal control method was selected for the research, which significantly reduces torque ripples and acoustic noise and is quite simple to implement. Inaccurate performance of the elements determining the position of the BLDC motor rotor causes a large error in the position estimation and has a negative impact on the operation of the drive controlled in this way. Using the developed control algorithms, it is possible to correctly determine the mechanical position of the rotor even for multi-pole motors. The proposed method is relatively easy to implement and does not require modification of control systems, being limited to changes only in the software of such devices. The tests of the actual system clearly show the usefulness of such a control method and its effectiveness.

scholarly journals Geometric Reduced-Attitude Control of Fixed-Wing UAVs

2021 ◽  
Vol 11 (7) ◽  
pp. 3147
Author(s):  
Erlend M. Coates ◽  
Thor I. Fossen
Keyword(s):  
Unmanned Aerial Vehicles ◽  
Attitude Control ◽  
Controller Design ◽  
State Of The Art ◽  
Model Structure ◽  
Practical Application ◽  
Ultimate Boundedness ◽  
Adaptive Backstepping ◽  
Control Effectiveness ◽  
Heading Angle

This paper presents nonlinear, singularity-free autopilot designs for multivariable reduced-attitude control of fixed-wing aircraft. To control roll and pitch angles, we employ vector coordinates constrained to the unit two-sphere and that are independent of the yaw/heading angle. The angular velocity projected onto this vector is enforced to satisfy the coordinated-turn equation. We exploit model structure in the design and prove almost global asymptotic stability using Lyapunov-based tools. Slowly-varying aerodynamic disturbances are compensated for using adaptive backstepping. To emphasize the practical application of our result, we also establish the ultimate boundedness of the solutions under a simplified controller that only depends on rough estimates of the control-effectiveness matrix. The controller design can be used with state-of-the-art guidance systems for fixed-wing unmanned aerial vehicles (UAVs) and is implemented in the open-source autopilot ArduPilot for validation through realistic software-in-the-loop (SITL) simulations.

Impact of diversifying media content on country's economic potential: case study of South Korea

2021 ◽  
Vol 7 (Extra-D) ◽  
pp. 187-199
Author(s):  
Alina Vitalievna Fadeeva ◽  
Daria Anatolevna Puiu ◽  
Pavel Yurievich Gurushkin ◽  
Sergey Borisovich Nikonov ◽  
Iuliia Valerievna Puiu
Keyword(s):  
South Korea ◽  
Effective Interaction ◽  
Modern Society ◽  
Creative Industries ◽  
Practical Significance ◽  
Creative Industry ◽  
Art Cinema ◽  
Software Products ◽  
Scientific Potential ◽  
The Moment

The popularity of Korean pop culture in the world can be considered an exceptional phenomenon of 2020. One should note that processes reflecting the effective interaction of state structures with the spheres of the creative industry in the modern economy have a special scientific potential at the moment. These creative industry spheres include art, cinema, animation, music, game development and software products. The most successful case in this area is the developed system of cultural media export in South Korea. Research into the economic opportunities of creative industries as a new stage in modern society is becoming a practically significant way to solve the problems of increasing the country's economic power in the Digital Age. The experience of South Korea is still insufficiently covered in Russian research. The practical significance of research in this field is associated with the study of the use of cultural products as a tool for economic growth.

Altitude Controller Design for Quadcopter UAV

2015 ◽  
Vol 74 (1) ◽  
Author(s):  
Muhammad Zaki Mustapa
Keyword(s):  
Real Time ◽  
Attitude Control ◽  
Controller Design ◽  
Design Method ◽  
Time Windows ◽  
The Real ◽  
Data Acquisition Card ◽  
Aerial Vehicle ◽  
Hovering Control ◽  
Real Time Application

This paper discusses on attitude control of a quadcopter unmanned aerial vehicle (UAV) in real time application. Newton-Euler equation is used to derive the model of system and the model characteristic is analyzed. The paper describes the controller design method for the hovering control of UAV automatic vertical take-off system. In order to take-off the quadcopter and stable the altitude, PID controller has been designed. The scope of study is to develop an altitude controller of the vertical take-off as realistic as possible. The quadcopter flight system has nonlinear characteristics. A simulation is conducted to test and analyze the control performance of the quadcopter model. The simulation was conducted by using Mat-lab Simulink. On the other hand, for the real time application, the PCI-1711 data acquisition card is used as an interface for controller design which routes from Simulink to hardware. This study showed the controller designs are implemented and tuned to the real system using Real Time Windows Target approach by Mat-Lab Simulink.

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