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Research Papers

An Adjustable Model Reference Adaptive Control for a Flexible Launch Vehicle

[+] Author and Article Information
A. M. Khoshnood1

Department of Mechanical Engineering, K. N. Toosi University of Technology, P.O. Box 19395-1999, Tehran 19991 43344, Irankhoshnood@dena.kntu.ac.ir

J. Roshanian

Department of Aerospace Engineering, K. N. Toosi University of Technology, P.O. Box 16765-3381, Tehran, Iranroshanian@kntu.ac.ir

A. A. Jafari

Department of Mechanical Engineering, K. N. Toosi University of Technology, P.O. Box 19395-1999, Tehran 19991 43344, Iranjafari@kntu.ac.ir

A. Khaki-Sedigh

Department of Electrical Engineering, K. N. Toosi University of Technology, P.O. Box 16315-1355, Tehran, Iransedigh@kntu.ac.ir

1

Corresponding author.

J. Dyn. Sys., Meas., Control 132(4), 041010 (Jun 18, 2010) (7 pages) doi:10.1115/1.4001709 History: Received December 25, 2008; Revised February 11, 2010; Published June 18, 2010; Online June 18, 2010

Flexibility and aeroelastic behaviors in large space structures can lead to degradation of control system stability and performance. The model reference adaptive notch filter is an effective methodology used and implemented for reducing such effects. In this approach, designing a model reference for adaptive control algorithm in a flight device such as a launch vehicle is very important. In this way, the vibrations resulting from the structure flexibility mostly affects the pitch channel, and its influences on the yaw channel are negligible. This property is used and also the symmetrical behavior of the yaw and pitch channels. In this paper, by using this property and also the symmetrical behavior of the yaw and pitch channels, a new model reference using identification on the yaw channel is proposed. This model behaves very similar to the rigid body dynamic of the pitch channel and can be used as a model reference to control the vibrational effects. Simulation results illustrated applies the proposed algorithm and considerably reduces the vibrations in the pitch channel. Moreover, the main advantage of this new method is the online tuning of the model reference against unforeseen variations in the parameters of the rigid launch vehicle, which has not been considered in the previous works. Finally, robustness of the new control system in the presence of asymmetric behavior is investigated.

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Copyright © 2010 by American Society of Mechanical Engineers
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Figures

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Figure 1

Definition of body and inertial vectors in the floating frame of reference method

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Figure 2

Block diagram of the new model reference adaptive notch filter for attitude control of the FLV

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Figure 3

Angle of actuator deflection in pitch channel with and without adaptive controller

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Figure 4

Pitch angular velocity with and without adaptive controller

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Figure 5

Magnifying the angle of actuator deflection in pitch channel

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Figure 6

Yaw angular velocity with and without adaptive controller (notice the negligible amplitude of vibration)

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Figure 7

Error of estimation between the new model reference and rigid dynamic model of the pitch channel

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Figure 8

Comparison of the error of frequency estimation in the new and the previous model reference approach

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Figure 9

Frequency estimation by using the new algorithm

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Figure 10

Estimation of transfer function coefficients of yaw channel for model reference

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Figure 11

The error between the actual and estimated model in the presence of asymmetric behavior

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