A hybrid switched mode control approach for V/STOL flight control problems

2002 ◽  
Author(s):  
N.H. McClamroch ◽  
I. Kolmanovsky
Keyword(s):  
Flight Control ◽  
Control Problems ◽  
Control Approach ◽  
Mode Control

scholarly journals Sliding Mode Control for Mass Moment Aerospace Vehicles Using Dynamic Inversion Approach

2013 ◽  
Vol 2013 ◽  
pp. 1-11 ◽  
Author(s):  
Xiao-Yu Zhang ◽  
Yu-Xin Zhao ◽  
De-Xin Xu ◽  
Kun-Peng He
Keyword(s):  
Sliding Mode Control ◽  
Flight Control ◽  
Sliding Mode ◽  
Moving Mass ◽  
Aerodynamic Parameter ◽  
Aerospace Vehicles ◽  
Variable Structure Systems ◽  
Control Approach ◽  
Mode Control ◽  
Mass Moment

The moving mass actuation technique offers significant advantages over conventional aerodynamic control surfaces and reaction control systems, because the actuators are contained entirely within the airframe geometrical envelope. Modeling, control, and simulation of Mass Moment Aerospace Vehicles (MMAV) utilizing moving mass actuators are discussed. Dynamics of the MMAV are separated into two parts on the basis of the two time-scale separation theory: the dynamics of fast state and the dynamics of slow state. And then, in order to restrain the system chattering and keep the track performance of the system by considering aerodynamic parameter perturbation, the flight control system is designed for the two subsystems, respectively, utilizing fuzzy sliding mode control approach. The simulation results describe the effectiveness of the proposed autopilot design approach. Meanwhile, the chattering phenomenon that frequently appears in the conventional variable structure systems is also eliminated without deteriorating the system robustness.

Design and flight test of active flutter suppression on the X-56A multi-utility technology test-bed aircraft

2016 ◽  
Vol 120 (1228) ◽  
pp. 893-909 ◽  
Author(s):  
E. L. Burnett ◽  
J. A. Beranek ◽  
B. T. Holm-Hansen ◽  
C. J. Atkinson ◽  
P. M. Flick
Keyword(s):  
Flight Control ◽  
Flight Test ◽  
Test Bed ◽  
Control Laws ◽  
Control Approach ◽  
Mode Control ◽  
Flying Qualities ◽  
Technical Challenges ◽  
Long Endurance ◽  
Aircraft Configurations

ABSTRACTEfforts to develop the next generation of aircraft with ever-increasing levels of performance – higher, farther, faster, cheaper – face great technical challenges. One of these technical challenges is to reduce structural weight of the aircraft. Another is to look to aircraft configurations that have been unrealizable to date. Both of these paths can lead to a rigid flex coupling phenomenon that can result in anything from poor flying qualities to the loss of an aircraft due to flutter. This has led to a need to develop an integrated flight and aeroelastic control capability where structural dynamics are included in the synthesis of flight control laws. Studies have indicated that the application of an integrated flight and aeroelastic control approach to a SensorCraft high-altitude long-endurance vehicle would provide substantial performance improvement(1,2). Better flying qualities and an expanded flight envelope through multi-flutter mode control are two areas of improvement afforded by integrated flight and aeroelastic control. By itself, multi-flutter mode control transforms the flutter barrier from a point of catastrophic structural failure to a benign region of flight. This paper discusses the history and issues associated with the development of such an integrated flight and aeroelastic control system for the X-56A aircraft.

A Communication-less Multi-mode Control Approach for Adaptive Power-Sharing in Ships-based Seaport Microgrid

2021 ◽  
pp. 1-1
Author(s):  
Muhammad Umair Mutarraf ◽  
Yacine Terriche ◽  
Mashood Nasir ◽  
Yajuan Guan ◽  
Chun-Lien Su ◽  
...  
Keyword(s):  
Power Sharing ◽  
Control Approach ◽  
Mode Control ◽  
Adaptive Power ◽  
Multi Mode

Automatic Flight Control of Unmanned Helicopter Based on Nonlinear Model

2012 ◽  
Vol 472-475 ◽  
pp. 1492-1499
Author(s):  
Run Xia Guo
Keyword(s):  
Nonlinear Model ◽  
Flight Control ◽  
Attitude Control ◽  
Lyapunov Stability Theory ◽  
Test Results ◽  
Unmanned Helicopter ◽  
Control Laws ◽  
Control Approach ◽  
State Dependent ◽  
Compensation Technique

The Unmanned helicopter (UMH) movement was divided into two parts, namely, attitude and trajectory motion. And then a two-timescale nonlinear model was established. The paper improved and expanded state dependent riccati equation (SDRE) control approach, deriving analytical conditions for achieving global asymptotic stability with lyapunov stability theory. Proof was given. By combining improved SDRE control with nonlinear feed-forward compensation technique, the full envelop flight attitude control laws could be designed. On the basis of attitude control, trajectory controller was developed. Actual flight tests were carried out. Test results show that the control strategy is highly effective.

Conditional integrator sliding mode control of an unmanned quadrotor helicopter

2021 ◽  
pp. 095965182110498
Author(s):  
Yohan Díaz-Méndez ◽  
Leandro Diniz de Jesus ◽  
Marcelo Santiago de Sousa ◽  
Sebastião Simões Cunha ◽  
Alexandre Brandão Ramos
Keyword(s):  
Sliding Mode Control ◽  
Transient Response ◽  
Tracking Control ◽  
Position Control ◽  
Sliding Mode ◽  
Control Technique ◽  
Control Law ◽  
Control Problems ◽  
Control Activity ◽  
Mode Control

Sliding mode control (SMC) is a widely used control law for quadrotor regulation and tracking control problems. The purpose of this article is to solve the tracking problem of quadrotors using a relatively novel nonlinear control law based on SMC that makes use of a conditional integrator. It is demonstrated by a motivation example that the proposed control law can improve the transient response and chattering shortcomings of the previous approaches of similar SMC based controllers. The adopted Newton–Euler model of quadrotor dynamics and controller design is treated separately in two subsystems: attitude and position control loops. The stability of the control technique is demonstrated by Lyapunov’s analysis and the effectiveness and performance of the proposed method are compared with a similar integral law, also based on SMC, and validated by tracking control problems using numerical simulations. Simulations were developed in the presence of external disturbances in order to evaluate the controller robustness. The effectiveness of the proposed controller was verified by performance indexes, demonstrating less accumulated tracking errors and control activity and improvement in the transient response and disturbance rejection when compared to a conventional integrator sliding mode controller.

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