Kalman filter based optimal control approach for attitude control of a missile

Nilanjan Patra; Kaushik Halder; Avijit Routh; Abhro Mukherjee; Satyabrata Das

doi:10.1109/ICCCI.2013.6466158

Kalman filter based optimal control approach for attitude control of a missile

Nilanjan Patra, Kaushik Halder, Avijit Routh, Abhro Mukherjee, Satyabrata Das

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

Abstract

The paper represents the Kalman Filter based optimal control approach to control the angle of attack of a missile attitude. The Kalman filter is used here to estimate the state of the system. A state feedback Linear Quadratic Gaussian controller which takes the filtered estimated states has been implemented into the system to control the angle of attack of the missile. The proposed method of controller takes care of the unwanted noise present in the system and ensures guaranteed convergence of the tracking error to zero as well. The performance of the proposed Kalman filter based controller has been evaluated with the presence of noise and disturbances in the system. Simulation results have been carried out to show the effectiveness of the controller.

Original language	English
Title of host publication	2013 International Conference on Computer Communication and Informatics
Publisher	Institute of Electrical and Electronics Engineers
Pages	1-4
Number of pages	4
DOIs	https://doi.org/10.1109/ICCCI.2013.6466158
Publication status	Published - 4 Jan 2013
Event	2013 International Conference on Computer Communication and Informatics - Coimbatore, India Duration: 4 Jan 2013 → 6 Jan 2013

Conference

Conference	2013 International Conference on Computer Communication and Informatics
Abbreviated title	ICCCI 2013
Country/Territory	India
City	Coimbatore
Period	4/01/13 → 6/01/13

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https://ieeexplore.ieee.org/abstract/document/6466158Licence: All Rights Reserved

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title = "Kalman filter based optimal control approach for attitude control of a missile",

abstract = "The paper represents the Kalman Filter based optimal control approach to control the angle of attack of a missile attitude. The Kalman filter is used here to estimate the state of the system. A state feedback Linear Quadratic Gaussian controller which takes the filtered estimated states has been implemented into the system to control the angle of attack of the missile. The proposed method of controller takes care of the unwanted noise present in the system and ensures guaranteed convergence of the tracking error to zero as well. The performance of the proposed Kalman filter based controller has been evaluated with the presence of noise and disturbances in the system. Simulation results have been carried out to show the effectiveness of the controller.",

author = "Nilanjan Patra and Kaushik Halder and Avijit Routh and Abhro Mukherjee and Satyabrata Das",

year = "2013",

month = jan,

day = "4",

doi = "10.1109/ICCCI.2013.6466158",

language = "English",

pages = "1--4",

booktitle = "2013 International Conference on Computer Communication and Informatics",

publisher = "Institute of Electrical and Electronics Engineers",

address = "United States",

note = "2013 International Conference on Computer Communication and Informatics, ICCCI 2013 ; Conference date: 04-01-2013 Through 06-01-2013",

}

Patra, N, Halder, K, Routh, A, Mukherjee, A & Das, S 2013, Kalman filter based optimal control approach for attitude control of a missile. in 2013 International Conference on Computer Communication and Informatics. Institute of Electrical and Electronics Engineers, pp. 1-4, 2013 International Conference on Computer Communication and Informatics, Coimbatore, India, 4/01/13. https://doi.org/10.1109/ICCCI.2013.6466158

TY - GEN

T1 - Kalman filter based optimal control approach for attitude control of a missile

AU - Patra, Nilanjan

AU - Halder, Kaushik

AU - Routh, Avijit

AU - Mukherjee, Abhro

AU - Das, Satyabrata

PY - 2013/1/4

Y1 - 2013/1/4

N2 - The paper represents the Kalman Filter based optimal control approach to control the angle of attack of a missile attitude. The Kalman filter is used here to estimate the state of the system. A state feedback Linear Quadratic Gaussian controller which takes the filtered estimated states has been implemented into the system to control the angle of attack of the missile. The proposed method of controller takes care of the unwanted noise present in the system and ensures guaranteed convergence of the tracking error to zero as well. The performance of the proposed Kalman filter based controller has been evaluated with the presence of noise and disturbances in the system. Simulation results have been carried out to show the effectiveness of the controller.

AB - The paper represents the Kalman Filter based optimal control approach to control the angle of attack of a missile attitude. The Kalman filter is used here to estimate the state of the system. A state feedback Linear Quadratic Gaussian controller which takes the filtered estimated states has been implemented into the system to control the angle of attack of the missile. The proposed method of controller takes care of the unwanted noise present in the system and ensures guaranteed convergence of the tracking error to zero as well. The performance of the proposed Kalman filter based controller has been evaluated with the presence of noise and disturbances in the system. Simulation results have been carried out to show the effectiveness of the controller.

U2 - 10.1109/ICCCI.2013.6466158

DO - 10.1109/ICCCI.2013.6466158

M3 - Conference contribution

SP - 1

EP - 4

BT - 2013 International Conference on Computer Communication and Informatics

PB - Institute of Electrical and Electronics Engineers

T2 - 2013 International Conference on Computer Communication and Informatics

Y2 - 4 January 2013 through 6 January 2013

ER -

Kalman filter based optimal control approach for attitude control of a missile

Abstract

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