NEAR OPTIMAL GUIDANCE FOR SHORT RANGE HOMING MISSILE,USING THE MINIMAL ORDER OBSERVER
Tantawy, M., El-Leithy, M. (1985). NEAR OPTIMAL GUIDANCE FOR SHORT RANGE HOMING MISSILE,USING THE MINIMAL ORDER OBSERVER. EKB Journal Management System, 1(A.S.A.T. CONFERENCE 14-16 May 1985 r CAIRO), 969-987. doi: 10.21608/asat.1985.26569
M. O. Tantawy; M. A. El-Leithy. "NEAR OPTIMAL GUIDANCE FOR SHORT RANGE HOMING MISSILE,USING THE MINIMAL ORDER OBSERVER". EKB Journal Management System, 1, A.S.A.T. CONFERENCE 14-16 May 1985 r CAIRO, 1985, 969-987. doi: 10.21608/asat.1985.26569
Tantawy, M., El-Leithy, M. (1985). 'NEAR OPTIMAL GUIDANCE FOR SHORT RANGE HOMING MISSILE,USING THE MINIMAL ORDER OBSERVER', EKB Journal Management System, 1(A.S.A.T. CONFERENCE 14-16 May 1985 r CAIRO), pp. 969-987. doi: 10.21608/asat.1985.26569
Tantawy, M., El-Leithy, M. NEAR OPTIMAL GUIDANCE FOR SHORT RANGE HOMING MISSILE,USING THE MINIMAL ORDER OBSERVER. EKB Journal Management System, 1985; 1(A.S.A.T. CONFERENCE 14-16 May 1985 r CAIRO): 969-987. doi: 10.21608/asat.1985.26569

NEAR OPTIMAL GUIDANCE FOR SHORT RANGE HOMING MISSILE,USING THE MINIMAL ORDER OBSERVER

International Conference on Aerospace Sciences and Aviation Technology
Article 78, Volume 1, A.S.A.T. CONFERENCE 14-16 May 1985 r CAIRO, May 1985, Page 969-987  XML PDF (2.6 MB)
Document Type: Original Article
DOI: 10.21608/asat.1985.26569
View on SCiNiTO View on SCiNiTO
Authors
M. O. Tantawy1; M. A. El-Leithy2
1M.T.C., Cairo, Egypt.
2Air Defence Forces Research Department.
Abstract
This paper brought a new trend giving a baseline algorithm which yield an approach for the design of the near optimal controller for the short range homing, guided missile. This new trend is based on the minimal order observer as state estimator. The problem is studied based on a linear discrete model taking into consideration the dynamics of the missile motion, the target manuvering capability, errors of measuring sensors and launch initial conditions. Quadratic criterion penalizing the state trajectory as well as the control is used. The near optimal control is derived through the linear quadratic Gaussian technique (L.Q.G.) and the minimal order observer as stato estimator. The derived control accounts for bounded control variable, Limited missile manuvering capability and bounded minimum terminal miss-distance at the intercept point.
Statistics
Article View: 92
PDF Download: 185