Proportional Guidance and CDM Control Synthesis for a Short-Range Homing Surface-to-Air Missile

AbstractThis paper presents a high-performance and simple guidance method for a short-range missile. Missile control systems are designed along the estimated flight envelope of the missile based on coefficient diagram method. The linear time invariant (LTI) models are obtained by linearizing missile...

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Bibliographic Details
Published inJournal of aerospace engineering Vol. 25; no. 2; pp. 168 - 177
Main Authors Budiyono, Agus, Rachman, Harapan
Format Journal Article
LanguageEnglish
Published American Society of Civil Engineers 01.04.2012
Subjects
Acceleration
Algebra
Coefficients
Design analysis
Invariants
Missiles
Proportional navigation
Surface to air missiles
Technical Papers
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Summary:AbstractThis paper presents a high-performance and simple guidance method for a short-range missile. Missile control systems are designed along the estimated flight envelope of the missile based on coefficient diagram method. The linear time invariant (LTI) models are obtained by linearizing missile nonlinear model at specific operating points. The governing equations of motion are accurately modeled by taking into account the effect of the mass rate and the center of gravity shift. A novel algebraic approach called coefficient diagram method (CDM) is used to design normal acceleration and roll angle control systems. The proportional navigation law is considered as the guidance law. One case of engagement scenarios is studied and the missile performance is evaluated. The robustness of the proposed controller is tested against parameter uncertainties and wind disturbance.
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ISSN:0893-1321
1943-5525
DOI:10.1061/(ASCE)AS.1943-5525.0000104