Three-Dimensional Trajectory Control via Nonlinear Adaptive Approach

2014 ◽  
Vol 635-637 ◽  
pp. 1285-1289
Author(s):  
Rong Jun Yang ◽  
Yun Guo Shi
Keyword(s):  
Sliding Mode ◽  
Control Point ◽  
Three Dimensional ◽  
Trajectory Control ◽  
Force Model ◽  
Reference Trajectory ◽  
Control Input ◽  
Model Errors ◽  
Nonlinear Controller ◽  
Dynamic Inverse

A representation of robust nonlinear controller is proposed for ammunitions space trajectory control, which is combined adaptive dynamic inverse with sliding mode control. The control law design accomplishes 3-D trajectory tracking using attitude angle as control input, and includes the parameter update to correct force model errors, also sliding mode switch portion to resist winds. A transition reference trajectory which is easy to implement for tracking is designed, according to the actual location and speed of start control point. Simulation results show the proposed control strategy get accurate tracking performance of excellent dynamic characteristics in large uncertainties.

Three-dimensional adaptive fixed-time guidance law against maneuvering targets with impact angle constraints and control input saturation

2021 ◽  
pp. 014233122110598
Author(s):  
Fei Ma ◽  
Yunjie Wu ◽  
Siqi Wang ◽  
Xiaofei Yang ◽  
Yueyang Hua
Keyword(s):  
Sliding Mode ◽  
Input Saturation ◽  
Three Dimensional ◽  
Fixed Time ◽  
Impact Angle ◽  
Guidance System ◽  
Control Input ◽  
Guidance Law ◽  
The Stability ◽  
And Control

This paper presents an adaptive fixed-time guidance law for the three-dimensional interception guidance problem with impact angle constraints and control input saturation against a maneuvering target. First, a coupled guidance model formulated by the relative motion equation is established. On this basis, a fixed-time disturbance observer is employed to estimate the lumped disturbances. With the help of this estimation technique, the adaptive fixed-time sliding mode guidance law is designed to accomplish accurate interception. The stability of the closed-loop guidance system is proven by the Lyapunov method. Simulation results of different scenarios are executed to validate the effectiveness and superiority of the proposed guidance law.

Direct Adaptive Fuzzy Moving Sliding Mode Proportional Integral Tracking Control of a Three-Dimensional Overhead Crane

2016 ◽  
Vol 138 (10) ◽  
Author(s):  
Tsung-Chih Lin ◽  
Yu-Chen Lin ◽  
Majid Moradi Zirkohi ◽  
Hsi-Chun Huang
Keyword(s):  
Tracking Control ◽  
Sliding Mode ◽  
Three Dimensional ◽  
Overhead Crane ◽  
Nonlinear Controller ◽  
Proportional Integral ◽  
Adaptive Fuzzy ◽  
Highly Nonlinear ◽  
Position Regulation ◽  
Robust Regulation

In this paper, a novel direct adaptive fuzzy moving sliding mode proportional integral (PI) tracking control of a three-dimensional (3D) overhead crane which is modeled by five highly nonlinear second-order ordinary differential equations is proposed. The fast and robust position regulation and antiswing control can be achieved based on the proposed approach. Due to universal approximation theorem, fuzzy control provides nonlinear controller, i.e., fuzzy logic controllers, to perform the unknown nonlinear control actions. Simultaneously, in order to achieve fast and robust regulation and to enhance robustness in the presence of disturbance and parameter variations, moving sliding mode control (SMC) is introduced to tradeoff between reaching phase and sliding phase. Hence, the sliding surface is moved by changing the magnitude of the slope by adaptive law and varying the intercept by tuning algorithm. Simulations performed using a scaled 3D mathematical model of the crane confirm that the proposed control scheme can keep the horizontal position of the payload invariable and suppress the swing of the payload effectively during the hoisting or lowing process.

Multiple Sliding Surface Control: Theory and Application

2000 ◽  
Vol 122 (4) ◽  
pp. 586-593 ◽  
Author(s):  
J. K. Hedrick ◽  
P. P. Yip
Keyword(s):  
Controller Design ◽  
Sliding Mode ◽  
Control Input ◽  
Sliding Surface ◽  
Nonlinear Controller ◽  
Automotive Control ◽  
Surface Control ◽  
Surface Method ◽  
Highly Nonlinear ◽  
Automated Highway

This paper discusses the development of a nonlinear controller design methodology and its application to an automotive control problem. The method is called the “Multiple Sliding Surface” method and is closely related to sliding mode control, input/output linearization and integrator backstepping. The method was developed for a class of systems, typical of automotive control systems, where the uncertainties are “mismatched” and where many of the equations contain sparse, experimentally obtained maps. The error bounds on these maps are often unknown and their sparseness makes them difficult to differentiate. The developed method does not require any derivatives and has guaranteed semi-global stability. This paper summarizes the development of the method and applies it to the design of a highly nonlinear system. The example is a combined brake/throttle controller for precision vehicle following. This controller was implemented on the California PATH vehicles in DEMO’97, an automated highway technology demonstration that occurred in San Diego, California in August of 1997. [S0022-0434(00)03004-5]

A Nonlinear Controller Design Method for Fuel-Injected Automotive Engines

1988 ◽  
Vol 110 (3) ◽  
pp. 313-320 ◽  
Author(s):  
D. Cho ◽  
J. K. Hedrick
Keyword(s):  
Fuel Injection ◽  
Control Method ◽  
Controller Design ◽  
Sliding Mode ◽  
Design Method ◽  
Model Errors ◽  
Nonlinear Controller ◽  
Engine Model ◽  
Automotive Engines ◽  
On Line

A nonlinear, “sliding mode” fuel-injection controller is designed based on a physically motivated, mathematical engine model. The designed controller can achieve a commanded air-to-fuel ratio with excellent transient properties, which offers the potential for improving fuel economy, torque transients, and emission levels. The controller is robust to model errors as well as to rapidly changing maneuvers of throttle and spark advance. The sliding mode control method offers a great potential for future engine control problems, since: it results in a relatively simple control structure that requires little on-line computing and no table lookups; it is robust to model errors and disturbances; and it can be easily adapted to a family of engines.

A Fault-Tolerant and Anti-Disturbance Control Based on Sliding Mode Iterative Learning Law for Attitude of Satellite

2013 ◽  
Vol 339 ◽  
pp. 10-15
Author(s):  
Jian Cheng LI ◽  
Tao Xi ◽  
Bo Wang
Keyword(s):  
Fault Tolerant ◽  
Sliding Mode ◽  
External Disturbance ◽  
Tracking Error ◽  
Iterative Learning ◽  
Reference Trajectory ◽  
Control Input ◽  
Orbit Control ◽  
On Line ◽  
Learning Law

To cope with the problem of the degradation of actuation effectiveness caused by actuator deflection or fault in the attitude and orbit control system (AOCS) of spacecraft on-orbit, an attitude fault-tolerant and anti-disturbance control scheme is proposed based on a sliding mode iterative learning law, in which the pseudo control input is applied to design the sliding mode controller to ensure the AOCS tracks a reference trajectory precisely after some fault occurred; By analyzing the Lyapunov stability, a novel adaptive iterative learning law is developed, which in term of the tracking error, determine some parameters in controller on-line to address the actuator failure and external disturbance. Numerical simulation experiments show that the fault-tolerant and anti-disturbance controller can ameliorate actuation malfunction and compensate the influence of external disturbance effectively.

scholarly journals Aeroelastic Dynamic Response and Control of an Aeroelastic System with Hysteresis Nonlinearities

2015 ◽  
Vol 2015 ◽  
pp. 1-10 ◽  
Author(s):  
Xingzhi Xu ◽  
Yakui Gao ◽  
Weiguo Zhang
Keyword(s):  
Time Delay ◽  
Control Method ◽  
Sliding Mode ◽  
State Feedback Control ◽  
Control Law ◽  
Control Input ◽  
Nonlinear Controller ◽  
Aeroelastic System ◽  
Flutter Suppression ◽  
Hysteresis Nonlinearity

A state feedback control law based on the sliding mode control method is derived for the aeroelastic response and flutter suppression of a two-dimensional airfoil section with hysteresis nonlinearity in pitch. An observer is constructed to estimate the unavailable state variables of the system. With the control law designed, nonlinear effect of time delay between the control input and actuator is investigated by a numerical approach. The closed-loop system including the observer and nonlinear controller is asymptotically stable. The simulation results show that the observer can give precise estimations for the plunge displacement and the velocities in pitch and plunge and that the controller is effective for flutter suppression. The time delay between the control input and actuator may jeopardize the control performance and cause high-frequency vibrations.

scholarly journals Bumpless Transfer of Uncertain Switched System and Its Application to Turbofan Engines

Energies ◽  
2021 ◽  
Vol 14 (16) ◽  
pp. 5204
Author(s):  
Penghui Sun ◽  
Xi Wang ◽  
Shubo Yang ◽  
Bei Yang ◽  
Huairong Chen ◽  
...  
Keyword(s):  
Sliding Mode ◽  
Average Dwell Time ◽  
Transient Behavior ◽  
Switched System ◽  
Control Input ◽  
Nonlinear Controller ◽  
Turbofan Engines ◽  
Nonlinear Control Problems ◽  
Bumpless Transfer ◽  
Flight Envelope

Nonlinear control problems in turbofan engines are challenging. No single nonlinear controller can achieve desired control effects in a full flight envelope, but in the case of multiple controllers, there exist problems in the bumpless transfer between different controllers. To this end, this paper presents a bumpless transfer mechanism for an uncertain switched system based on integral sliding mode control (ISMC), and the mechanism can be used for the speed control of turbofan engines. The uncertain switched system is used to describe the turbofan engine dynamics. Then, the ISMC controller is derived for subsystems of the uncertain switched system. A resetting scheme is introduced for the ISMC controller to ensure the continuity of control inputs during the controller transition, as well as the bumpless transfer. In view of the transient behavior caused by controller switching, the global stability of the switched system is analyzed using the multiple Lyapunov function approach and average dwell time condition. Simulation results validate that the designed resetting scheme can ensure the continuity of control input signals and avoid the instability caused by high-frequency controller switching, and increase the control effectiveness of the proposed ISMC method within the full flight envelope.

Optimum Design for the Frame of Open Type Abrasive Flow Polish Machine

2012 ◽  
Vol 497 ◽  
pp. 89-93
Author(s):  
Liang Liang Yuan ◽  
Ke Hua Zhang ◽  
Li Min
Keyword(s):  
Finite Element ◽  
Natural Frequency ◽  
Finite Element Methods ◽  
Optimization Design ◽  
Low Cost ◽  
Three Dimensional ◽  
Force Model ◽  
Optimization Analysis ◽  
Open Type ◽  
Set Up

In order to process heterotype hole of workpiece precisely, an open abrasive flow polish machine is designed, and the optimization design of machine frame is done for low cost. Firstly, basing on the parameters designed with traditional ways, three-dimensional force model is set up with the soft of SolidWorks. Secondly, the statics and modal analysis for machine body have been done in Finite element methods (FEM), and then the optimization analysis of machine frame has been done. At last, the model of rebuild machine frame has been built. Result shows that the deformation angle value of machine frame increased from 0.72′ to 1.001′, the natural frequency of the machine decreased from 75.549 Hz to 62.262 Hz, the weight of machine decreased by 74.178 Kg after optimization. It meets the strength, stiffness and angel stiffness requirement of machine, reduces the weight and cost of machine.

Sign in / Sign up

Export Citation Format

Share Document