M., W., Matta, N., Kassem, W. (1993). CONTROL SYSTEM DESIGEN TECHNIQUES FOR GUIDED MISSILES. test, 5(ASAT CONFERENCE 4 - 6 May 1993, CAIRO), 359-371. doi: 10.21608/asat.1993.25637
Wagih M. M.; N. R. Matta; Wahid Kassem. "CONTROL SYSTEM DESIGEN TECHNIQUES FOR GUIDED MISSILES". test, 5, ASAT CONFERENCE 4 - 6 May 1993, CAIRO, 1993, 359-371. doi: 10.21608/asat.1993.25637
M., W., Matta, N., Kassem, W. (1993). 'CONTROL SYSTEM DESIGEN TECHNIQUES FOR GUIDED MISSILES', test, 5(ASAT CONFERENCE 4 - 6 May 1993, CAIRO), pp. 359-371. doi: 10.21608/asat.1993.25637
M., W., Matta, N., Kassem, W. CONTROL SYSTEM DESIGEN TECHNIQUES FOR GUIDED MISSILES. test, 1993; 5(ASAT CONFERENCE 4 - 6 May 1993, CAIRO): 359-371. doi: 10.21608/asat.1993.25637

CONTROL SYSTEM DESIGEN TECHNIQUES FOR GUIDED MISSILES

International Conference on Aerospace Sciences and Aviation Technology
Article 30, Volume 5, ASAT CONFERENCE 4 - 6 May 1993, CAIRO, May 1993, Pages 359-371    PDF (2.79 M)
Document Type: Original Article
DOI: 10.21608/asat.1993.25637
Authors
Wagih M. M.1; N. R. Matta2; Wahid Kassem3
1Ph. D. student, Air Defence Forces.
2Doctor Eng.
3A. Prof. Chair of Elect. Equip. And Armament Of A/C, Cairo M.T.C.
Abstract
The goal of this paper is a quantitative comparison of two autopilot designs for the same high-performance advanced guided missiles. One design is obtained using the linear quadratic optimum control technique of state-space design methodology. The other design is based on use of conventional design methods of pole-placement, root locus and frequency response, both designs are initiated with the same set of requirements for the same vehicle. The comparison considers not only robustness of design but also the complexity of implementing the two designs and the analysis required to validate each design.
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