Study and Realization of a Prototype Octocopter System with PID Controller

2018 ◽  
Vol 10 (4) ◽  
Author(s):  
Saidi Hemza ◽  
Djebri Boualem
Keyword(s):  
Dynamic Model ◽  
Pid Controller ◽  
External Environment ◽  
Lagrangian Model ◽  
System Dynamic Model ◽  
Proportional Integral Derivative ◽  
Proportional Integral Derivative Controller ◽  
Proportional Integral ◽  
Euler Model ◽  
Electrical Components

In this work, the mechanical and electrical components are designed and realised for an octocopter. The designed system dynamic model is supported with Euler-Lagrangian model and Newton-Euler model respectively for the rotational and transnational movements of the drone. The prototype octocopter is also equipped with a proportional integral derivative controller to feedback both location and respond to the external environment.

An application of Newton-like algorithm for H∞ proportional–integral–derivative controller synthesis of seesaw-cart system

2021 ◽  
pp. 014233122110638
Author(s):  
Vladimir Milic ◽  
Srecko Arandia-Kresic ◽  
Mihael Lobrovic
Keyword(s):  
Pid Controller ◽  
Optimality Criterion ◽  
Controller Synthesis ◽  
Laboratory Model ◽  
Linear Matrix ◽  
Proportional Integral Derivative ◽  
Backpropagation Algorithm ◽  
Proportional Integral Derivative Controller ◽  
Proportional Integral ◽  
Standard Linear

This paper is concerned with the synthesis of proportional–integral–derivative (PID) controller according to the [Formula: see text] optimality criterion for seesaw-cart system. The equations of dynamics are obtained through modelling a seesaw-cart system actuated by direct-current motor via rack and pinion mechanism using the Euler–Lagrange approach. The obtained model is linearised and synthesis of the PID controller for linear model is performed. An algorithm based on the sub-gradient method, the Newton method, the self-adapting backpropagation algorithm and the Adams method is proposed to calculate the PID controller gains. The proposed control strategy is tested and compared with standard linear matrix inequality (LMI)-based method on computer simulations and experimentally on a laboratory model.

scholarly journals Simulation of a Self-Balancing Platform on the Mobile Car

2021 ◽  
Vol 17 (3) ◽  
pp. 29-44
Author(s):  
Bushra Amer Tawfeeq ◽  
Maher Yahya Salloom ◽  
Ahmed Alkamachi
Keyword(s):  
Dynamic Model ◽  
Pid Controller ◽  
The Self ◽  
Simple Design ◽  
Proportional Integral Derivative ◽  
Simulated Model ◽  
Proportional Integral ◽  
Road Disturbance ◽  
Simulation Results ◽  
Biomedical Fields

        In the last years, the self-balancing platform has become one of the most common candidates to use in many applications such as flight, biomedical fields, industry. This paper introduced the simulated model of a proposed self-balancing platform that described the self–balancing attitude in (X-axis, Y-axis, or both axis) under the influence of road disturbance. To simulate the self-balanced platform's performance during the tilt, an integration between Solidworks, Simscape, and Simulink toolboxes in MATLAB was used. The platform's dynamic model was drawn in SolidWorks and exported as a STEP file used in the Simscape Multibody environment. The system is controlled using the proportional-integral-derivative (PID) controller to maintain the platform leveled and compensate for any road disturbances. Several road disturbances scenarios were designed in the x-axis, y-axis, or both axis (the pitch and roll angles) to examine the controller effectiveness. The simulation results indicate that that the platform completed self-balancing under the effect of disturbance (10° and -10°) on the X-axis, Y-axis, and both axes in less than two milliseconds. Therefore, a proposed self-balancing platform's simulated model has a high self-balancing accuracy and meets operational requirements despite its simple design.  

Delay margin computation of generator excitation control system by using fractional order controller

2020 ◽  
Vol 42 (13) ◽  
pp. 2465-2474
Author(s):  
Halil Erol
Keyword(s):  
Control System ◽  
Time Delay ◽  
Fractional Order ◽  
Pid Controller ◽  
Excitation Control ◽  
Proportional Integral Derivative ◽  
Proportional Integral Derivative Controller ◽  
Proportional Integral ◽  
Generator Excitation Control ◽  
Delay Margin

This article is devoted to stability analysis of generator excitation control system that has some time delay with fractional order proportional integral derivative controller by using direct method. When the time delay exceeds certain critical values, the excitation control system becomes unstable. In order to obtain more delay margin, in control part of the system, fractional order proportional integral derivative controller is used. A formulation is obtained to find out the maximum time delay which is known as delay margin with which the system can tolerate without any loss in its stability. All the possible stability regions analytically in the parametric space of the time delay is obtained by using an exact method and it is presented in this study. The method is formulated in frequency domain. The time-domain simulations are implemented to validate theoretical delay margin results in Matlab/Simulink. When it is compared with previous researches in literature, better stability margin is obtained. The results have shown that fractional order PID controller gives wide stability area than integer order PID controller.

PERANCANGAN UJI SIRIP ROKET BAGIAN AILERON DENGAN MENGGUNAKAN KONTROL PID

2018 ◽  
Vol 14 (1) ◽  
pp. 1-11
Author(s):  
Galih Irfan Firdaus
Keyword(s):  
Proportional Integral Derivative ◽  
Accelerometer Sensor ◽  
Proportional Integral Derivative Controller ◽  
Proportional Integral

Roket merupakan sebuah peluru kendali atau suatu kendaraan terbang yang mendapatkan dorongan melalui reaksi roket secara cepat dengan bahan fluida dari keluaran mesin roket. Sistem Kendali Sirip Roket berbasis Mikrokontroller ATmega8 berguna untuk mengendalikan sirip roket khususnya bagian aileron.  Dibutuhkan komponen – komponen pendukung berupa Sensor Accelerometer, Sensor Gyroscope, ATmega8 dan Motor Servo. Alat pengendali sirip roket ini dapat digunakan untuk mengendalikan sirip roket bagian aileron pada saat posisi roket tidak stabil atau terjadi gerakan naik turun pada saat setelah diluncurkan, sehingga dapat menghasilkan penerbangan yang maksimal dalam mencapai sasaran.Perancangan yang  digunakan adalah jenis pengendalian dengan kontrol PID. PID (Proportional Integral Derivative controller) merupakan kontroller untuk menentukan presisi suatu sistem instrumentasi dengan karakteristik adanya umpan balik pada sistem tesebut. Pengontrol PID adalah pengontrol konvensional yang banyak dipakai dalam dunia industri. Karakteristik pengontrol PID sangat dipengaruhi oleh kontribusi besar dari ketiga parameter P, I dan D. Pemilihan konstanta Kp, Ki dan Kd akan mengakibatkan penonjolan sifat dari masing-masing elemen. Dalam perancangan sebuah sistem kendali menggunakan kontroller PID pada motor servo yang diharapkan mampu menggerakkan sirip naik dan sirip turun pada roket sehingga mampu menjaga kestabilan roket saat diluncurkan. Prosentase error pada proyek akhir ini adalah 0,5 %.Roket merupakan sebuah peluru kendali atau suatu kendaraan terbang yang mendapatkan dorongan melalui reaksi roket secara cepat dengan bahan fluida dari keluaran mesin roket. Sistem Kendali Sirip Roket berbasis Mikrokontroller ATmega8 berguna untuk mengendalikan sirip roket khususnya bagian aileron.  Dibutuhkan komponen – komponen pendukung berupa Sensor Accelerometer, Sensor Gyroscope, ATmega8 dan Motor Servo. Alat pengendali sirip roket ini dapat digunakan untuk mengendalikan sirip roket bagian aileron pada saat posisi roket tidak stabil atau terjadi gerakan naik turun pada saat setelah diluncurkan, sehingga dapat menghasilkan penerbangan yang maksimal dalam mencapai sasaran.Perancangan yang  digunakan adalah jenis pengendalian dengan kontrol PID. PID (Proportional Integral Derivative controller) merupakan kontroller untuk menentukan presisi suatu sistem instrumentasi dengan karakteristik adanya umpan balik pada sistem tesebut. Pengontrol PID adalah pengontrol konvensional yang banyak dipakai dalam dunia industri. Karakteristik pengontrol PID sangat dipengaruhi oleh kontribusi besar dari ketiga parameter P, I dan D. Pemilihan konstanta Kp, Ki dan Kd akan mengakibatkan penonjolan sifat dari masing-masing elemen. Dalam perancangan sebuah sistem kendali menggunakan kontroller PID pada motor servo yang diharapkan mampu menggerakkan sirip naik dan sirip turun pada roket sehingga mampu menjaga kestabilan roket saat diluncurkan. Prosentase error pada proyek akhir ini adalah 0,5 %.

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