scholarly journals A Novel Emergent State Control Law for an Integrated Helicopter/Turboshaft Engine System

2014 ◽  
Vol 2014 ◽  
pp. 1-14 ◽  
Author(s):  
Haibo Zhang ◽  
Yongjin Li ◽  
S. Deng
Keyword(s):  
Flight Control ◽  
Dynamic Performance ◽  
Control Law ◽  
State Control ◽  
Closed Loop System ◽  
Helicopter Control ◽  
Control Loops ◽  
Fuel Flow ◽  
Control Scheme ◽  
Turboshaft Engine

A two-layer robust control scheme is proposed to get a better response ability for emergency maneuvers of helicopter. Note that the power used in ascending flight is the main coupling between helicopter and its turboshaft engines; therefore vertical flight control is separated from conventional helicopter control loops and combined with fuel flow and turbine bleeding to new control loops denoted as an inner layer, whereas the mission level flight control is as the out layer. A conclusion in global asymptotically tracking for devising this new scheme is firstly derived from a Generalized Gronwall-Bellman approach. Due to this integrated designing, not only is the helicopter better controlled, but also much better power rapid tracking is realized for engines. Simulations are conducted to validate the new scheme in emergent ascending and descending flights, and the results illustrate that the response time of the closed-loop system is dramatically reduced when compared to the traditional one. Moreover, the presented system also has better dynamic performance under inferences.

The Research on Height Control of Airship with Constant Flying Speed

2014 ◽  
Vol 644-650 ◽  
pp. 875-878
Author(s):  
Xin Li Zhang ◽  
Yun An Hu ◽  
Di Liu
Keyword(s):  
Nonlinear Model ◽  
Flight Control ◽  
Pid Control ◽  
Simulation Analysis ◽  
Reference Value ◽  
Control Law ◽  
High Increase ◽  
Height Control ◽  
Control Scheme ◽  
Detailed Simulation

The PID control scheme of airship with fixed flying high is studied in allusion to pitch channel nonlinear model of a class of stratosphere airship in this paper. The traditional PID control law is designed aim at the fixed high flight control of airship. The detailed simulation analysis is presented. It indicates that the airship can realize the fixed high flight in the range of 1000 meters. When flying high increase further, PID control scheme is not reasonable because instruction is too large. At the same time, the speed of engine has large influence on PID control scheme. The research of paper has good technical reference value for design and experiments of stratosphere airship.

scholarly journals Robust dynamic inversion control of flight control system based on L1 adaptive structure

2021 ◽  
Vol 39 (5) ◽  
pp. 995-1004
Author(s):  
Yu LI ◽  
Xiaoxiong LIU ◽  
Ruichen MING ◽  
Shaoshan SUN ◽  
Weiguo ZHANG
Keyword(s):  
Control System ◽  
Flight Control ◽  
Dynamic Performance ◽  
Dynamic Inversion ◽  
Control Law ◽  
Flight Control System ◽  
Parameter Uncertainties ◽  
Strong Robustness ◽  
Adaptive Structure ◽  
The Stability

Nonlinear Dynamic Inversion(NDI) control has excellent rapidity and decoupling ability, unfortunately it lacks the essential robustness to disturbance. From the perspective of enhancing the robustness, an adaptive NDI method based on L1 adaptive structure is proposed. The L1 adaptive structure is introduced into the NDI control to enhance its robustness, which also guarantees the stability and expected dynamic performance of the system suffering from the disturbance influence. Secondly, the flight control law of the advanced aircraft is designed based on the present method to improve the robustness and fault tolerance of the flight control system. Finally, the effectiveness of the flight control law based on the present approach is verified under the fault disturbance. The results showed that the flight control law based on L1 adaptive NDI has excellent dynamic performance and strong robustness to parameter uncertainties and disturbances.

Adaptive Control of Uncertain Gun Control System of Tank

2011 ◽  
Vol 88-89 ◽  
pp. 88-92 ◽  
Author(s):  
Lu Juan Shen ◽  
Ye Bao ◽  
Jian Ping Cai
Keyword(s):  
Adaptive Control ◽  
Control System ◽  
Gun Control ◽  
Control Law ◽  
Uncertain Parameters ◽  
Simulation Studies ◽  
Closed Loop System ◽  
Control Scheme ◽  
The Stability ◽  
Adaptive Control Law

In this paper, a class of gun control system of tank is considered with uncertain parameters and the backlash-like hysteresis which modeled by a differential equation. An adaptive control law is designed with backstepping technique. Compared to exist results on tank gun control problem , in our control scheme, the effect of backlash hysteresis is considered completely than to be linearized simply and no knowledge is assumed on the uncertain parameters. the stability of closed loop system and the tracking performance can be guaranteed by this control law. Simulation studies show that this controller is effective.

scholarly journals Hybrid velocity/force control for robot navigation in compliant unknown environments

Robotica ◽  
2006 ◽  
Vol 24 (6) ◽  
pp. 745-758 ◽  
Author(s):  
Dushyant Palejiya ◽  
Herbert G. Tanner
Keyword(s):  
Lyapunov Functions ◽  
Closed Loop ◽  
Position Control ◽  
Dynamic Control ◽  
Control Law ◽  
Closed Loop System ◽  
Multiple Lyapunov Functions ◽  
Unknown Environments ◽  
Control Scheme ◽  
Novel Method

We combine a “hybrid” force-/position-control scheme with a potential field approach into a novel method for collision recovery and navigation in unknown environments. It can be implemented both on manipulators and mobile robots. The use of force sensors allows us to locally sense the environment and design a dynamic control law. Multiple Lyapunov functions are used to establish asymptotic stability of the closed-loop system. The switching conditions and stability criteria are established under reasonable assumptions on the type of obstacles present in the environment. Extensive simulation results are presented to illustrate the system behavior under the designed control scheme, and verify its stability, collision recovery, and navigation properties.

Direct Adaptive Control of Faulty UAVs via Quantum Feedforward and Fuzzy Feedback

2011 ◽  
Vol 130-134 ◽  
pp. 1973-1977 ◽  
Author(s):  
Fu Yang Chen ◽  
Bin Jiang ◽  
Changan Jiang
Keyword(s):  
Adaptive Control ◽  
Flight Control ◽  
Quantum Control ◽  
Control Method ◽  
Dynamic Performance ◽  
Adaptive Controller ◽  
Control Technique ◽  
Control Law ◽  
Flight Control System ◽  
Direct Adaptive Control

In this paper, the control law designing of longitudinal-lateral attitude and faults self-repairing against the UAVs are analyzed. The direct adaptive controller via fuzzy feedback is designed to guarantee the UAVs stabe and having good flying performance. Then, a new direct adaptive control method is formulated by quantum control technique. Consequently, not only the stable error but the property of response and robustness is improved well. Simulation results are given to illustrate that a good dynamic performance of the flight control system with large faults can be maintained with the proposed control method.

scholarly journals Saturating Stiffness Control of Robot Manipulators with Bounded Inputs

2017 ◽  
Vol 27 (1) ◽  
pp. 79-90 ◽  
Author(s):  
María del Carmen Rodríguez-Liñán ◽  
Marco Mendoza ◽  
Isela Bonilla ◽  
César A. Chávez-Olivares
Keyword(s):  
Closed Loop ◽  
Robot Manipulator ◽  
Robot Manipulators ◽  
Contact Forces ◽  
Control Law ◽  
Closed Loop System ◽  
Control Scheme ◽  
Lyapunov Stability Analysis ◽  
Stiffness Control ◽  
Three Degree Of Freedom

AbstractA saturating stiffness control scheme for robot manipulators with bounded torque inputs is proposed. The control law is assumed to be a PD-type controller, and the corresponding Lyapunov stability analysis of the closed-loop equilibrium point is presented. The interaction between the robot manipulator and the environment is modeled as spring-like contact forces.The proper behavior of the closed-loop system is validated using a three degree-of-freedom robotic arm.

Autonomous Mission Management Based Nonlinear Flight Control Design for a Class of Hybrid Unmanned Aerial Vehicles

2021 ◽  
Vol 01 (02) ◽  
pp. 2150009
Author(s):  
Kemao Peng
Keyword(s):  
Flight Control ◽  
Closed Loop ◽  
Main Idea ◽  
Loop System ◽  
Control Law ◽  
Closed Loop System ◽  
Control Laws ◽  
Mission Management ◽  
Rotary Wing ◽  
Transition Flight

In this paper, a nonlinear flight control law is designed for a hybrid unmanned aerial vehicle (UAV) to achieve the advanced flight performances with the autonomous mission management (AMM). The hybrid UAV is capable of hovering like quadrotors and maneuvering as fixed-wing aircraft. The main idea is to design the flight control laws in modules. Those modules are organized online by the autonomous mission management. Such online organization will improve the UAV autonomy. One of the challenges is to execute the transition flight between the rotary-wing and fixed-wing modes. The resulting closed-loop system with the designed flight control law is verified in simulation and the simulation results demonstrate that the resulting closed-loop system can successfully complete the designated flight missions including the transition flight between the rotary-wing and fixed-wing modes.

Non-linear multivariable flight control of aircraft

1998 ◽  
Vol 212 (2) ◽  
pp. 137-144 ◽  
Author(s):  
S E Lyshevski
Keyword(s):  
Flight Control ◽  
Closed Loop ◽  
Dynamic Performance ◽  
Optimization Procedure ◽  
Loop System ◽  
Closed Loop System ◽  
Bounded Control ◽  
Performance Improvements ◽  
Non Linear ◽  
Linear Differential

Innovative design methods are needed for advanced aircraft in response to requirements towards substantial performance improvements. Functionally and operationally, the aircraft must be considered as the highly coupled non-linear multi-input multi-output system, i.e. the aerodynamics have to be mapped by non-linear differential or difference equations. To improve flying and handling qualities, to increase manœuvrability and to expand the operating envelope, an innovative optimization procedure is developed to design the constrained controllers for multi-input multi-output aircraft. In particular, a bounded control law is synthesized by employing the Hamilton-Jacobi theory, and the admissibility concept is used to study the stability of the resulting closed-loop system. The developed optimization procedure is applied to a non-linear ninth-order model of an AFTI/F-16 aircraft. A bounded controller is designed, and modelling results are presented to demonstrate the dynamic performance of the resulting closed-loop system.

scholarly journals Finite-time control for uncertain systems and application to flight control

2020 ◽  
Vol 25 (2) ◽  
Author(s):  
Fang Wang ◽  
Jianmei Wang ◽  
Kun Wang ◽  
Changchun Hua ◽  
Qun Zong
Keyword(s):  
Flight Control ◽  
Finite Time ◽  
Sliding Mode ◽  
Lyapunov Stability Theory ◽  
Fixed Time ◽  
Closed Loop System ◽  
Finite Time Stability ◽  
Time Control ◽  
Control Scheme ◽  
Mismatched Uncertainty

In this paper, the finite-time control design problem for a class of nonlinear systems with matched and mismatched uncertainty is addressed. The finite-time control scheme is designed by integrating multi power reaching (MPR) law and finite-time disturbance observer (FTDO) into integral sliding mode control, where a novel sliding surface is designed, and the FTDO is applied to estimate the uncertainty. Then the fixed-time reachability of the MPR law is analyzed, and the finite-time stability of the closed-loop system is proven in the framework of Lyapunov stability theory. Finally, numerical simulation and the application to the flight control of hypersonic vehicle (HSV) are provided to show the effectiveness of the designed controller.

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