scholarly journals Modeling and Control of Torso Compass Gait Biped Robot with AI Controller

2017 ◽  
Vol 13 (1) ◽  
pp. 32-37
Author(s):  
Abbas Miry
Keyword(s):  
Degrees Of Freedom ◽  
Biped Robot ◽  
Optimization Method ◽  
Genetic Optimization ◽  
Modeling And Control ◽  
Optimal Value ◽  
Result Show ◽  
The Matrix ◽  
And Control ◽  
The Mathematical Model

This work presents the mathematical model for a torso compass gait biped robot with three degrees of freedom (DOF) which is comprised of two legs and torso. Euler Lagrange method's is used to drive the dynamic equation of robot with computed control is used as a controller. The relative angles are used to simplify the robot equation and get the symmetry of the matrix. Convention controller uses critical sampling to find the value of KP and Kv in computed controller, in this paper the Genetic optimization method is used to find the optimal value of KP and Kv with suitable objective function which employ the error and overshoot to make the biped motion smooth as possible. To investigate the work of robot a Matlab 2013b is used and the result show success of modeling.

Dynamic Modeling and Control Techniques for a Quadrotor

2019 ◽  
pp. 20-66
Author(s):  
Heba Elkholy ◽  
Maki K. Habib
Keyword(s):  
Pid Controller ◽  
Degrees Of Freedom ◽  
Sliding Mode ◽  
Dynamic Performance ◽  
Simulation Environment ◽  
Modeling And Control ◽  
Controller Gain ◽  
Aerial Vehicle ◽  
And Control ◽  
The Mathematical Model

This chapter presents the detailed dynamic model of a Vertical Take-Off and Landing (VTOL) type Unmanned Aerial Vehicle (UAV) known as the quadrotor. The mathematical model is derived based on Newton Euler formalism. This is followed by the development of a simulation environment on which the developed model is verified. Four control algorithms are developed to control the quadrotor's degrees of freedom: a linear PID controller, Gain Scheduling-based PID controller, nonlinear Sliding Mode, and Backstepping controllers. The performances of these controllers are compared through the developed simulation environment in terms of their dynamic performance, stability, and the effect of possible disturbances.

Dynamic Modeling and Control Techniques for a Quadrotor

2015 ◽  
pp. 408-454
Author(s):  
Heba Elkholy ◽  
Maki K. Habib
Keyword(s):  
Pid Controller ◽  
Degrees Of Freedom ◽  
Sliding Mode ◽  
Dynamic Performance ◽  
Simulation Environment ◽  
Modeling And Control ◽  
Controller Gain ◽  
Aerial Vehicle ◽  
And Control ◽  
The Mathematical Model

This chapter presents the detailed dynamic model of a Vertical Take-Off and Landing (VTOL) type Unmanned Aerial Vehicle (UAV) known as the quadrotor. The mathematical model is derived based on Newton Euler formalism. This is followed by the development of a simulation environment on which the developed model is verified. Four control algorithms are developed to control the quadrotor's degrees of freedom: a linear PID controller, Gain Scheduling-based PID controller, nonlinear Sliding Mode, and Backstepping controllers. The performances of these controllers are compared through the developed simulation environment in terms of their dynamic performance, stability, and the effect of possible disturbances.

Automated System of Stabilization and Position Control of Aviation Equipment

2019 ◽  
pp. 297-330
Author(s):  
Olha Sushchenko
Keyword(s):  
Position Control ◽  
Transfer Functions ◽  
Controller Design ◽  
Robust Stabilization ◽  
Automated System ◽  
Simulink Model ◽  
The Matrix ◽  
Stabilized Platform ◽  
And Control ◽  
The Mathematical Model

In this chapter, the author presents the problems of design of the robust automated system for stabilization and control of platforms with aircraft observation equipment. The mathematical model of the triaxial stabilized platform is developed. The procedure of synthesis of robust stabilization system based on robust structural synthesis is represented. The above-mentioned procedure uses loop-shaping approach and method of the mixed sensitivity. The matrix weighting transfer functions are obtained. The optimization programs in MatLab are developed. The developed procedures are approved based on the results of simulation by means of the appropriate Simulink model. The obtained results can be useful for unmanned aerial vehicles and aircraft of special aviation, which are used for monitoring technical objects and aerial photography. The technical contributions are procedures of the robust controller design represented as the flowchart. The proposed approach is validated by application of the theoretical suppositions to the concrete example and appropriate simulation results.

Isolation Application of Controlled and Uncontrolled Magnetorheological Dampers for Random Base Excitaion

2005 ◽  
Author(s):  
A. Narimani ◽  
M. F. Golnaraghi
Keyword(s):  
Base Isolation ◽  
Mr Damper ◽  
Optimization Method ◽  
Experimental Results ◽  
Base Excitation ◽  
Modeling And Control ◽  
Isolation Systems ◽  
Active Damper ◽  
Suspension Model ◽  
And Control

This paper presents experimental investigation of modeling and control of magnetorhological damper for transient base excitation inputs. Force characteristics of a commercially available MR damper (RD-1005-3) for shock and other transient base excitation are analytically obtained and validated using a scaled suspension model. The proposed model characterizes damper behavior more accurately and efficiently for analytical applications. The time and frequency responses of the developed model are compared with the experimental results and show good agreement. Finally, using the RMS optimization method the performance of the system for different types of controllers is compared with the optimal values of linear isolator system. Experimental results show that the performance of base isolation systems for transient and shock inputs significantly improves by utilizing a controlled semi-active damper over uncontrolled MR damper or an optimally designed passive isolator.

Gust Response Parameter Optimization of Two-Dimensional Airfoil Section

2013 ◽  
Vol 344 ◽  
pp. 55-60
Author(s):  
Ying Bi ◽  
Zhi Gang Wu ◽  
Chao Yang
Keyword(s):  
Parameter Optimization ◽  
Degrees Of Freedom ◽  
Aircraft Design ◽  
Optimization Method ◽  
System Response ◽  
Two Dimensional ◽  
Airfoil Section ◽  
Response Parameter ◽  
The Matrix ◽  
Simulated Calculation

Taking the two-dimensional airfoil section model with two degrees of freedom as the object, this paper develops a multi-parameter optimization method, which regards the minimum system response under the given gust disturbances as the objective function and gives the expression describing the state space form of response sensitivity in which the matrix parameter sensitivity solution obtained by CVD method, further more, the Newton iteration method based on the sensitivity is adopted to realize the parameter optimization. By the simulated calculation of numerical examples and comparing with the conventional method, the optimization method has the advantage of better calculation efficiency and robustness and being used for aircraft design.

scholarly journals Modeling and Control of Crane Overload Protection During Marine Lifting Operation Based on Model Predictive Control

2017 ◽  
Author(s):  
Zhengru Ren ◽  
Roger Skjetne ◽  
Zhen Gao
Keyword(s):  
Model Predictive Control ◽  
Predictive Control ◽  
Pid Controller ◽  
Degrees Of Freedom ◽  
Multiple Shooting ◽  
Control Input ◽  
Lumped Mass ◽  
Modeling And Control ◽  
Overload Protection ◽  
And Control

This paper deals with a nonlinear model predictive control (NMPC) scheme for a winch servo motor to overcome the sudden peak tension in the lifting wire caused by a lumped-mass payload at the beginning of a lifting off or a lowering operation. The crane-wire-payload system is modeled in 3 degrees of freedom with the Newton-Euler approach. Direct multiple shooting and real-time iteration (RTI) scheme are employed to provide feedback control input to the winch servo. Simulations are implemented with MATLAB and CaSADi toolkit. By well tuning the weighting matrices, the NMPC controller can reduce the snatch loads in the lifting wire and the winch loads simultaneously. A comparative study with a PID controller is conducted to verify its performance.

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