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Calculus Model for a Rolling Guided Missile

École de technologie supérieure, Département de génie de la production automatisée, 1100 Notre Dame Ouest, Montréal, Québec, Canada, H3C 1K3

V. Chelaru

Uzina Electromecanic, Ploieti, Romania

P. Parvu

Universitatea Politehnica Bucureti, Facultatea de Inginerie Aerospaial, Bucureti, Romania

C. Gheorghe

Uzina Electromecanic, Ploieti, Romania

The paper presents the relations that form the basis for the calculus models needed to study rolling guided missiles. The equations of the general motion are written within the Resal trihedral in a way that allows, after linearization, one to draw up a structural scheme of the controlled object, a scheme that will be used in the guided missile system analysis. Opposite to the flying machines with stabilized roll where the analysis is done after decoupling the channels, for the missile with rotation, the analysis of the scheme is done simultaneously on both channels, as terms used are complex terms. Furthermore, there will be presented some characteristics of this type of missile by analyzing a model close to the one of an antichariot missile with gasodynamic control.

Key Words: Guidance • control • missiles • gasodynamics • flight quality • aerodynamics

Journal of Vibration and Control, Vol. 7, No. 6, 863-889 (2001)
DOI: 10.1177/107754630100700606


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