scholarly journals A Simple Attitude Control of Quadrotor Helicopter Based on Ziegler-Nichols Rules for Tuning PD Parameters

2014 ◽  
Vol 2014 ◽  
pp. 1-13 ◽  
Author(s):  
ZeFang He ◽  
Long Zhao
Keyword(s):  
Linear System ◽  
Attitude Control ◽  
Feedback Linearization ◽  
Linear Part ◽  
The Other ◽  
Pd Controller ◽  
Control Effect ◽  
Nonlinear Part ◽  
Nonlinear Controllers ◽  
Attitude Controller

An attitude control strategy based on Ziegler-Nichols rules for tuning PD (proportional-derivative) parameters of quadrotor helicopters is presented to solve the problem that quadrotor tends to be instable. This problem is caused by the narrow definition domain of attitude angles of quadrotor helicopters. The proposed controller is nonlinear and consists of a linear part and a nonlinear part. The linear part is a PD controller with PD parameters tuned by Ziegler-Nichols rules and acts on the quadrotor decoupled linear system after feedback linearization; the nonlinear part is a feedback linearization item which converts a nonlinear system into a linear system. It can be seen from the simulation results that the attitude controller proposed in this paper is highly robust, and its control effect is better than the other two nonlinear controllers. The nonlinear parts of the other two nonlinear controllers are the same as the attitude controller proposed in this paper. The linear part involves a PID (proportional-integral-derivative) controller with the PID controller parameters tuned by Ziegler-Nichols rules and a PD controller with the PD controller parameters tuned by GA (genetic algorithms). Moreover, this attitude controller is simple and easy to implement.

Forecasting of Summer Monsoon Rainfall over Gangetic West Bengal, India Utilising Intrinsic Mode Functions, Linear and Neural Regression

2020 ◽  
Vol 12 (1) ◽  
pp. 60-69 ◽  
Author(s):  
Pijush Basak
Keyword(s):  
Neural Network ◽  
West Bengal ◽  
Monsoon Rainfall ◽  
Linear Part ◽  
Intrinsic Mode Functions ◽  
Quasi Biennial Oscillation ◽  
Nonlinear Part ◽  
South West ◽  
South West Monsoon ◽  
West Monsoon

The South West Monsoon rainfall data of the meteorological subdivision number 6 of India enclosing Gangetic West Bengal is shown to be decomposable into eight empirical time series, namely Intrinsic Mode Functions. This leads one to identify the first empirical mode as a nonlinear part and the remaining modes as the linear part of the data. The nonlinear part is modeled with the technique Neural Network based Generalized Regression Neural Network model technique whereas the linear part is sensibly modeled through simple regression method. The different Intrinsic modes as verified are well connected with relevant atmospheric features, namely, El Nino, Quasi-biennial Oscillation, Sunspot cycle and others. It is observed that the proposed model explains around 75% of inter annual variability (IAV) of the rainfall series of Gangetic West Bengal. The model is efficient in statistical forecasting of South West Monsoon rainfall in the region as verified from independent part of the real data. The statistical forecasts of SWM rainfall for GWB for the years 2012 and 2013 are108.71 cm and 126.21 cm respectively, where as corresponding to the actual rainfall of 93.19 cm 115.20 cm respectively which are within one standard deviation of mean rainfall.

scholarly journals Further Discoveries of Cretan and Aegean Script: with Libyan and Proto-Egyptian Comparisons

1897 ◽  
Vol 17 ◽  
pp. 327-393 ◽  
Author(s):  
A. J. Evans
Keyword(s):  
Linear System ◽  
The Other ◽  
Greek Letter ◽  
Other Hand ◽  
The One

In a former communication attention was called to an indigenous system of writing in Crete, the earlier stages of which go back, not only far beyond the date of the first introduction of the Phoenician alphabet among the Greeks, but to a period considerably anterior to the most ancient monumental record of the Semitic letters.From the evidence of ancient Cretan seals it was possible to demonstrate the existence of a form of pictographic writing from its simplest beginnings to a more conventional and abbreviated stage. Side by side with this a variety of data supplied by seals, vases, and inscribed stones, showed the further existence of a linear system of writing, connected with the other and presenting some striking comparisons on the one hand with certain characters found by Professor Petrie in Egypt and by Mr. Bliss at Lachish; on the other hand with the syllabic script of Cyprus and some Anatolian regions. It was further pointed out that in some instances Cretan linear characters displayed a remarkable correspondence with Phoenician and early Greek letter forms.

Exploring research on high-speed vehicle attitude control with plasma virtual flap manipulation

2018 ◽  
Vol 233 (10) ◽  
pp. 3627-3634
Author(s):  
Wang Xin ◽  
Yan Jie ◽  
Zhang Yerong
Keyword(s):  
Attitude Control ◽  
High Speed ◽  
Long Duration ◽  
Aerodynamic Control ◽  
Control Authority ◽  
Attitude Controller ◽  
Lift And Drag ◽  
Cruise Flight ◽  
Aerodynamic Lift ◽  
High Speed Vehicle

This work provides an attitude solution for a high-speed vehicle using plasma aerodynamic control called “plasma virtual flap” manipulation. This paper describes the concept of using plasma active control as plasma virtual flap for off-design attitude manipulation problem. Design of an attitude controller considering plasma aerodynamic effects for the high-speed vehicle is presented. The aerodynamic lift and drag force features in the high speed, long duration cruise flight with plasma actuator effect are introduced, where the estimated models and attitude controller are established. This paper documents the development and capabilities of plasma virtual flap attitude control authority. Simulation results are presented to exhibit the effectiveness of the proposed method.

Design of a New Nonlinear Excitation Controller Combined Differential Geometry with PID Theory

2012 ◽  
Vol 588-589 ◽  
pp. 1507-1511
Author(s):  
Xiao Juan Sun
Keyword(s):  
Differential Geometry ◽  
Single Machine ◽  
Feedback Linearization ◽  
Transient Stability ◽  
Infinite System ◽  
System Simulation ◽  
Control Effect ◽  
Nonlinear Excitation ◽  
Terminal Voltage ◽  
Simulation Results

This paper presents a nonlinear excitation controller for transient stability combined differential geometry theory with PID technology. The controller ties the output of linear multi-variable excitation controller with the output of PID. Exact feedback linearization theory of differential geometry is applied to the design of linear multi-variable excitation controller for the single machine infinite system. Simulation results show that, compared with the general differential geometric controller, the proposed controller has the better control effect on power system and which remarkably improves the terminal voltage deficiencies in the control of generator.

Research on Attitude Control of Spacecraft Based on ADRC

2011 ◽  
Vol 383-390 ◽  
pp. 358-365 ◽  
Author(s):  
Fu Lin Teng ◽  
Hong Yu Ge ◽  
Hong Sheng Li ◽  
Jian Hua Zhang
Keyword(s):  
Attitude Control ◽  
Disturbance Rejection ◽  
High Performance ◽  
Control Technology ◽  
Attitude Control System ◽  
Active Disturbance Rejection ◽  
Disturbance Rejection Control ◽  
Simulation And Experiment ◽  
Attitude Controller ◽  
Very High

Modern spacecraft demands from an attitude control system very high performance and accuracy, and many new features, such as disturbance rejection capability. The recently developed active disturbance rejection control technology is applied to the attitude control of spacecraft subject to disturbances and parametric uncertainties. Simulation and experiment show significant advantages of the proposed attitude controller over the controller resulting from conventional PID approach.

scholarly journals Design of High Pointing Accuracy NPSAT-1 Satellite Attitude Systems of Armature Controlled DC Motor with utilization for PD Controller

2020 ◽  
Vol 12 (1) ◽  
pp. 145-156
Author(s):  
M. RAJA ◽  
O. PRAKASH
Keyword(s):  
Control System ◽  
Control Systems ◽  
Attitude Control ◽  
Settling Time ◽  
Pd Controller ◽  
Reference Orbit ◽  
Satellite Attitude ◽  
Satellite Attitude Control ◽  
Leo Satellites ◽  
Pointing Accuracy

An Attitude control system plays the important role to maintain the satellite to desired attitude orientations. The intended application of NANO satellite in low earth orbits (LEO) helps find transient responses with and without controllers. LEO satellites typically orbit at an altitude ranging between160-2000 km. LEO satellites are widely used for remote sensing, navigation, and military surveillance applications. The Nano NPSAT-1 satellite attitude control systems (ACS) are described in this research work. The high pointing accuracy attitude estimation and feedback control systems are presented. The design specifications have been taken to meet the accuracy requirements (desired value ≤ 0.2 seconds) of Nano satellite attitude control. The feedback signal from on-board sensors compared with reference orbit trajectory and implementation of the Proportional Derivative (PD) controller is constructed. An algorithm of Nano satellite (NPSAT-1) attitude control is implemented using MATLAB Tools. In addition, the closed loop poles help find the gain of the system using Root Locus (RL) methods. The satellite control system is used to improve the transient response like overshoot and settling time of the system. Thus, the design of attitude control to improve the rise time, the settling time, the maximum overshoot, and no steady state error was carried out.

Adaptive Attitude Controller Design for a Rigid Satellite with Feedback Linearization Approach

2020 ◽  
Vol 67 (4) ◽  
pp. 1445-1469
Author(s):  
Akram Adnane ◽  
Abdellatif Bellar ◽  
Mohammed Arezki Si Mohammed ◽  
Jiang Hong ◽  
Zoubir Ahmed Foitih
Keyword(s):  
Feedback Linearization ◽  
Controller Design ◽  
Attitude Controller ◽  
Feedback Linearization Approach

Attitude Controller Design of Multiple Independently Targeted Reentry Vehicle Based on Internal Model Control

2013 ◽  
Vol 462-463 ◽  
pp. 809-814
Author(s):  
Fei Zhao ◽  
Fan Li ◽  
Jian Hui Zhao
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Internal Model ◽  
Internal Model Control ◽  
Attitude Dynamics ◽  
Attitude Control System ◽  
Reentry Vehicle ◽  
Model Control ◽  
Internal Model Controller ◽  
Attitude Controller

A Multiple Independently Targeted Reentry Vehicle (MIRV) is a ballistic missile payload containing several warheads each capable of hitting one of a group of targets. In the process of missile flight control, the release of warheads brings about coupling to the missile attitude control system which will lower the flight stability. In order to solve this problem, a missile attitude controller, which combined the α-order integral inverse system with internal model principle, was presented. Firstly, determine the Post Boost Vehicle (PBV) attitude dynamics model. Then, combine the linearization of attitude dynamics equation with feed-forward decoupling method to implement the attitude decoupling. Finally, a two-degree of freedom (TOF) multivariable internal model controller was set up to optimize the control system performance. Simulation results show that the coupling of attitude control system has been eliminated. Compared with the original system, the internal model controller provides the control system better input-tracking performance, robust stability and interference suppression capacity.

Sign in / Sign up

Export Citation Format

Share Document