Technical gazette, Vol. 23 No. 3, 2016.
Original scientific paper
https://doi.org/10.17559/TV-20130625173047
Modified guidance law based on a sliding mode controller for a missile guidance system
Ali Amer Ahmed Alrawi
; School of Computer and Communication Engineering, d/a School of Manufacturing Engineering Complex, Universiti Malaysia Perlis (UniMAP), 1st Floor, Pauh Putra Main Campus, 02600 Arau, Perlis, Malaysia
Stevica Graovac
; University of Belgrade, School of Electrical Engineering, Bulevar kralja Aleksandra 73, 11000 Belgrade, Serbia
R. Badlishah Ahmad
; School of Computer and Communication Engineering, d/a School of Manufacturing Engineering Complex, Universiti Malaysia Perlis (UniMAP), 1st Floor, Pauh Putra Main Campus, 02600 Arau, Perlis, Malaysia
Md. Mijanur Rahman
; School of Computer and Communication Engineering, d/a School of Manufacturing Engineering Complex, Universiti Malaysia Perlis (UniMAP), 1st Floor, Pauh Putra Main Campus, 02600 Arau, Perlis, Malaysia
Abstract
mode controller (MSMC) algorithm is adopted to enable the missile to reach the desired target within a short period of time. The target always makes high manoeuvres when the missile is close to it. This issue has been treated in guidance and control (G&C) by using a MSMC instead of the traditional method such as proportional navigation method (PN).Theoretical analysis is conducted to reduce the miss-distance and chattering phenomenon in SMC. Simulation of MGCSMC compared with PN method shows an improvement of about 80 %, 47 % and 20 % for the chattering, miss-distance and finite time, respectively. Furthermore, for the high-altitude target, the MGCSMC improves the acceleration and flight angle of the missile by approximately 65 %, and achieves 100 % accuracy, whereas in PN method only 60 % accuracy is achieved under the same conditions.
Keywords
guidance and control systems; missile control; proportional navigation; robustness; sliding mode
Hrčak ID:
160121
URI
Publication date:
19.6.2016.
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