Novel Control Scheme for Helicopter Flight: Fuzzy Immune Adaptive Model Inversion Control

2008 ◽  
Vol 41 (2) ◽  
pp. 15046-15051 ◽  
Author(s):  
Zhao Jia ◽  
Chen Shenggong ◽  
Shen Gongzhang
Keyword(s):  
Adaptive Model ◽  
Model Inversion ◽  
Helicopter Flight ◽  
Control Scheme

scholarly journals Improving a real-time helicopter simulator model with linear input filters

2021 ◽  
Author(s):  
Pavle Šćepanović ◽  
Frederik A. Döring
Keyword(s):  
Feedback Control ◽  
Time Domain ◽  
Flight Test ◽  
Flight Mechanics ◽  
Mean Square ◽  
Qualification Test ◽  
Model Inversion ◽  
Helicopter Flight ◽  
The Time Domain ◽  
Mean Square Errors

AbstractFor a broad range of applications, flight mechanics simulator models have to accurately predict the aircraft dynamics. However, the development and improvement of such models is a difficult and time consuming process. This is especially true for helicopters. In this paper, two rapidly applicable and implementable methods to derive linear input filters that improve the simulator model are presented. The first method is based on model inversion, the second on feedback control. Both methods are evaluated in the time domain, compared to recorded helicopter flight test data, and assessed based on root mean square errors and the Qualification Test Guide bounds. The best results were achieved when using the first method.

Adaptive Model Inversion Flight Control for Tilt-Rotor Aircraft

1999 ◽  
Vol 22 (3) ◽  
pp. 402-407 ◽  
Author(s):  
Rolf T. Rysdyk ◽  
Anthony J. Calise
Keyword(s):  
Flight Control ◽  
Adaptive Model ◽  
Model Inversion ◽  
Tilt Rotor

Structured Adaptive Model Inversion Controller for Mars Atmospheric Flight

2008 ◽  
Vol 31 (4) ◽  
pp. 937-953 ◽  
Author(s):  
Carolina Restrepo ◽  
John Valasek
Keyword(s):  
Adaptive Model ◽  
Model Inversion

scholarly journals Event-Triggered Compound Learning Tracking Control of Nonstrict-Feedback Nonlinear Systems in Sensor-to-Controller Channel

2021 ◽  
Author(s):  
Yingjie Deng ◽  
Tao Ni ◽  
Jiantao Wang
Keyword(s):  
Tracking Control ◽  
Learning Algorithm ◽  
Approximation Error ◽  
Learning Performance ◽  
Time Varying ◽  
Adaptive Model ◽  
Control Laws ◽  
Virtual Control ◽  
Control Scheme ◽  
Event Triggered

Abstract This paper investigates the event-triggered tracking control of the nonstrict-feedback nonlinear system with the time-varying disturbances. While the fuzzy logic systems (FLSs) serve as the approximators to the unknown dynamics, the compound disturbance is comprised of the time-varying disturbance and the approximation error of the FLS. An event-triggered compound learning algorithm is originally developed to accurately estimate the total uncertainties. By referring to an event-triggered adaptive model, the control laws are derived without provoking the problem of "algebraic loop", seeing Remark 3. The command filters are employed to generate the continuous substitutes for both the virtual control laws and their derivatives, so as to solve the recently proposed problem of "jumps of virtual control laws" arising in the backstepping-based event-triggered control (ETC) that functions in the channel of sensor to controller. The triggering condition is constructed to guarantee the similarity between the adaptive model and the original system. While the satisfactory learning performance of the FLSs and the compound disturbances estimation are maintained, the proposed control scheme can guarantee the semi-globally uniformly ultimate boundedness (SGUUB) of all the tracking errors. Finally, a numerical experiment is carried out to exemplify the effectiveness of the proposed control scheme.

A Self-Repairing Control for the Uncertain System of a Helicopter Using Adaptive Sliding Mode Technology

2012 ◽  
Vol 468-471 ◽  
pp. 529-533 ◽  
Author(s):  
Fu Yang Chen ◽  
Wen Li Luan ◽  
Rui Hou
Keyword(s):  
Control System ◽  
Flight Control ◽  
Sliding Mode ◽  
Nonlinear Function ◽  
Uncertain System ◽  
Flight Control System ◽  
Adaptive Technology ◽  
Helicopter Flight ◽  
Control Scheme ◽  
Adaptive Control Scheme

In this paper, an adaptive control scheme is proposed for the uncertain flight control system of the helicopter with fault in vertical flight. The controller is designed using sliding mode theory and adaptive technology. In the controller, the nonlinear function is brought in, which can enlarge the small errors, and saturate the large errors. And it can make sure the good transient performances and stability of the helicopter flight control system. Finally, the simulation results of the nonlinear helicopter flight system illustrate the effectiveness and feasibility of the proposed scheme in the paper.

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