Feedback Linearization Based Generalized Predictive Control of Jupiter Icy Moons Orbiter

2008 ◽  
Vol 131 (1) ◽  
Author(s):  
Jianjun Shi ◽  
Atul G. Kelkar
Keyword(s):  
Dynamic Model ◽  
Predictive Control ◽  
Attitude Control ◽  
Nonlinear Dynamic ◽  
Feedback Linearization ◽  
Hybrid Control ◽  
Generalized Predictive Control ◽  
Concept Design ◽  
Nonlinear Dynamic Model ◽  
Icy Moons

This paper presents a nonlinear dynamic model of Jupiter Icy Moons Orbiter (JIMO), a concept design of a spacecraft intended to orbit the three icy moons of Jupiter, namely, Europa, Ganymede, and Callisto. The work in this paper represents a part of the feasibility study conducted to assess control requirements for the JIMO mission. A nonlinear dynamic model of JIMO is derived, which includes rigid body as well as flexible body dynamics. This paper presents a novel hybrid control strategy, which combines feedback linearization with generalized predictive control methodology in a two-step approach for attitude control of the spacecraft. This feedback linearization based generalized predictive control (FLGPC) law is used to accomplish a representative realistic in-orbit maneuver to test the efficacy of the controller. The controller performance shows that the FLGPC is a viable methodology for attitude control of a similar class of spacecraft. The results presented are a part of exhaustive study conducted to evaluate various controller designs.

A Dissipative Control Design for Jupiter Icy Moons Orbiter

2007 ◽  
Vol 129 (4) ◽  
pp. 559-565 ◽  
Author(s):  
Jianjun Shi ◽  
Atul G. Kelkar
Keyword(s):  
Dynamic Model ◽  
Nonlinear Dynamic ◽  
Concept Design ◽  
Nonlinear Dynamic Model ◽  
Icy Moons ◽  
Guaranteed Stability ◽  
Body Dynamics ◽  
Dissipative Control ◽  
Flexible Body Dynamics ◽  
Exhaustive Study

This technical brief presents a nonlinear dynamic model of Jupiter Icy Moons Orbiter (JIMO), a concept design of a spacecraft intended to orbit the three icy moons of Jupiter, namely, Europa, Ganymede, and Callisto. The work presented in this paper represents a part of a feasibility study conducted to assess control requirements of the JIMO mission. A nonlinear dynamic model of JIMO is derived that includes rigid body as well as flexible body dynamics. A nonlinear dissipative control law with guaranteed stability is used to perform a representative in-orbit maneuver. The results presented are part of an exhaustive study conducted to evaluate various controller designs.

scholarly journals The Quadrotor Dynamic Modeling and Indoor Target Tracking Control Method

2014 ◽  
Vol 2014 ◽  
pp. 1-9 ◽  
Author(s):  
Dewei Zhang ◽  
Hui Qi ◽  
Xiande Wu ◽  
Yaen Xie ◽  
Jiangtao Xu
Keyword(s):  
Target Tracking ◽  
Dynamic Model ◽  
Nonlinear Dynamic ◽  
Tracking Control ◽  
Feedback Linearization ◽  
Control Method ◽  
Measurement Unit ◽  
Control Algorithms ◽  
Nonlinear Dynamic Model ◽  
And Control

A reliable nonlinear dynamic model of the quadrotor is presented. The nonlinear dynamic model includes actuator dynamic and aerodynamic effect. Since the rotors run near a constant hovering speed, the dynamic model is simplified at hovering operating point. Based on the simplified nonlinear dynamic model, the PID controllers with feedback linearization and feedforward control are proposed using the backstepping method. These controllers are used to control both the attitude and position of the quadrotor. A fully custom quadrotor is developed to verify the correctness of the dynamic model and control algorithms. The attitude of the quadrotor is measured by inertia measurement unit (IMU). The position of the quadrotor in a GPS-denied environment, especially indoor environment, is estimated from the downward camera and ultrasonic sensor measurements. The validity and effectiveness of the proposed dynamic model and control algorithms are demonstrated by experimental results. It is shown that the vehicle achieves robust vision-based hovering and moving target tracking control.

scholarly journals Dynamic Modeling and Control of Electromechanical Coupling for Mechanical Elastic Energy Storage System

2013 ◽  
Vol 2013 ◽  
pp. 1-11 ◽  
Author(s):  
Yang Yu ◽  
Zengqiang Mi
Keyword(s):  
Energy Storage ◽  
Dynamic Model ◽  
Elastic Energy ◽  
Nonlinear Dynamic ◽  
Feedback Linearization ◽  
Electromechanical Coupling ◽  
Storage System ◽  
Electromechanical System ◽  
Nonlinear Dynamic Model ◽  
And Control

The structural scheme of mechanical elastic energy storage (MEES) system served by permanent magnet synchronous motor (PMSM) and bidirectional converters is designed. The aim of the research is to model and control the complex electromechanical system. The mechanical device of the complex system is considered as a node in generalized coordinate system, the terse nonlinear dynamic model of electromechanical coupling for the electromechanical system is constructed through Lagrange-Maxwell energy method, and the detailed deduction of the mathematical model is presented in the paper. The theory of direct feedback linearization (DFL) is applied to decouple the nonlinear dynamic model and convert the developed model from nonlinear to linear. The optimal control theory is utilized to accomplish speed tracking control for the linearized system. The simulation results in three different cases show that the proposed nonlinear dynamic model of MEES system is correct; the designed algorithm has a better control performance in contrast with the conventional PI control.

Analysis of Tourism Ecology Capacity Based on the Nonlinear Dynamic Model

2009 ◽  
Vol 11 (2) ◽  
pp. 163-168
Author(s):  
Long LV ◽  
Zhenfang HUANG ◽  
Jiang WU
Keyword(s):  
Dynamic Model ◽  
Nonlinear Dynamic ◽  
Nonlinear Dynamic Model

scholarly journals Development, Modeling and Control of a Dual Tilt-Wing UAV in Vertical Flight

Drones ◽  
2020 ◽  
Vol 4 (4) ◽  
pp. 71
Author(s):  
Luz M. Sanchez-Rivera ◽  
Rogelio Lozano ◽  
Alfredo Arias-Montano
Keyword(s):  
Dynamic Model ◽  
Attitude Control ◽  
Test Bench ◽  
Aerodynamic Coefficients ◽  
Nonlinear Dynamic Model ◽  
Modeling And Control ◽  
Drag And Lift ◽  
And Control ◽  
Dynamics Method ◽  
Indoor And Outdoor

Hybrid Unmanned Aerial Vehicles (H-UAVs) are currently a very interesting field of research in the modern scientific community due to their ability to perform Vertical Take-Off and Landing (VTOL) and Conventional Take-Off and Landing (CTOL). This paper focuses on the Dual Tilt-wing UAV, a vehicle capable of performing both flight modes (VTOL and CTOL). The UAV complete dynamic model is obtained using the Newton–Euler formulation, which includes aerodynamic effects, as the drag and lift forces of the wings, which are a function of airstream generated by the rotors, the cruise speed, tilt-wing angle and angle of attack. The airstream velocity generated by the rotors is studied in a test bench. The projected area on the UAV wing that is affected by the airstream generated by the rotors is specified and 3D aerodynamic analysis is performed for this region. In addition, aerodynamic coefficients of the UAV in VTOL mode are calculated by using Computational Fluid Dynamics method (CFD) and are embedded into the nonlinear dynamic model. To validate the complete dynamic model, PD controllers are adopted for altitude and attitude control of the vehicle in VTOL mode, the controllers are simulated and implemented in the vehicle for indoor and outdoor flight experiments.

Non-Linear Control of Tilting-Quadcopter Using Feedback Linearization Based Motion Control

2014 ◽  
Author(s):  
Alireza Nemati ◽  
Manish Kumar
Keyword(s):  
Control System ◽  
Dynamic Model ◽  
Motion Control ◽  
Feedback Linearization ◽  
Linear Control ◽  
Control Architecture ◽  
Simulation Studies ◽  
Nonlinear Dynamic Model ◽  
Feedback Linearization Control ◽  
Arbitrary Trajectory

In this paper, a nonlinear control of a tilting rotor quadcopter is presented. The overall control architecture is divided into two sub-controllers. The first controller is based on the feedback linearization control derived from the dynamic model of the tilting quadcopter. This controls the pitch, roll, and yaw motions required for movement along an arbitrary trajectory in space. The second controller is based on two PD controllers which are used to control the tilting of the quadcopter independently along the pitch and the yaw directions respectively. The overall control enables the quadcopter to combine tilting and movement along a desired trajectory simultaneously. Simulation studies are presented based on the developed nonlinear dynamic model of the tilting rotor quadcopter to demonstrate the validity and effectiveness of the overall control system for an arbitrary trajectory tracking.

Sign in / Sign up

Export Citation Format

Share Document