An experimental study of performance and fault-tolerance of a hybrid free-flight control scheme

2007 ◽  
pp. 449-463 ◽  
Author(s):  
Antonio Bicchi
Keyword(s):  
Experimental Study ◽  
Fault Tolerance ◽  
Flight Control ◽  
Free Flight ◽  
Control Scheme

High-Sideslip Model Reference Adaptive Flight Control for Aileron Locked Aircraft

2014 ◽  
Vol 651-653 ◽  
pp. 751-756
Author(s):  
Peng Fei Cheng ◽  
Cheng Fu Wu ◽  
Yue Guo
Keyword(s):  
Flight Control ◽  
Control Method ◽  
Reference Model ◽  
Sideslip Angle ◽  
Model Reference ◽  
Control Scheme ◽  
Adaptive Flight Control ◽  
Random Initialization ◽  
Model Reference Adaptive ◽  
The Given

This paper develops a high-sideslip flight control scheme based on model reference adaptive control (MRAC) to stabilize aircraft under aileron deadlock of one side. Firstly, the cascaded flight control scheme for high-sideslip straight flight is presented and how the control signals transfer is also analyzed. After that, the control structure and laws of MRAC for attitude inner-loop connected with sideslip command are designed. Finally, the control scheme is verified under a nonlinear aircraft model in conditions of no fault and one side aileron deadlock respectively. The simulation results show that when one side aileron deadlock occurs in accompany with the plant’s aerodynamic data perturbation and random initialization of controller parameters, this control method could utilize operation points of no-fault aircraft to force the faulty aircraft following the given reference model responses and finally tracking given sideslip angle command without static error robustly.

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.

High Altitude Airship Flight Control System Design and Simulation

2011 ◽  
Vol 128-129 ◽  
pp. 142-145
Author(s):  
Yong Hua Fan ◽  
Xin Li ◽  
Yun Feng Yu
Keyword(s):  
Control System ◽  
High Altitude ◽  
System Design ◽  
Flight Control ◽  
Control System Design ◽  
Flight Control System ◽  
Compound Control ◽  
Control Scheme ◽  
Self Tuning

The high altitude airship can not have desired performance to control the altitude rapidly and accurately when the elevator or ancillary air bursa charge or deflation is used only, because the elevator has little efficiency when the velocity is low and auxiliary air bursas charge or deflation control is very slow. It is present a method to design flight control system for a high altitude airship using auxiliary air bursas charge or deflation and elevator combination control. This combination control scheme is that the ancillary air bursa and elevator are also used to control the airship attitude to get large raise velocity and the ancillary air bursa control is used to adjust the airship altitude for suspension. In this paper, a high altitude airship model with compound control of elevator and ancillary air bursa charge and deflation is given firstly. Then the combination controller is designed by using fuzzy self-tuning control. Finally, it has been proved by simulation that the flight control system has desirable performance and the compound control scheme is feasible.

An Insect Tether System Using Magnetic Levitation: Development, Analysis and Feedback Control

2016 ◽  
Author(s):  
Shih-Jung Hsu ◽  
Yagız Efe Bayiz ◽  
Pan Liu ◽  
Bo Cheng
Keyword(s):  
System Identification ◽  
Feedback Control ◽  
Flight Control ◽  
Insect Flight ◽  
Magnetic Levitation ◽  
Body Movement ◽  
Whole Body ◽  
Free Flight ◽  
Tethered Flight ◽  
Development Analysis

Insect flight has gained wide interests in both biology and engineering communities in the past decades regarding its aerodynamics, sensing and flight control. However, studying insect flight experimentally remains a challenge in both free-flight and tethered-flight settings. In free flight experiments, due to highly unpredictable and fast flight behavior of flying insects, it is difficult to apply controlled sensory inputs to their flight system for system identification and modeling analyses. In tethered flight experiments, constrained whole body movement results in silenced proprioceptive feedback therefore breaks the flight control loop and does not reveal any flight dynamics. Therefore, this work aims to develop a novel insect tether system using magnetic levitation. Such a system magnetically fixes an insect in space but allows it to rotate freely about yaw axis with minimal interference from mechanical constraints. This paper presents the development, analysis and feedback control of this system and finally test its performance using a hawkmoth (Manduca Sexta). In addition, a system identification of the magnetic levitation system and detailed analysis in closed-loop stability and performance are provided. In the future, the insect tether system will be applied to study the insect flight aerodynamics, sensing and control.

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.

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