Taking initial aiming error as inertial small perturbance, we established a model of guidance loop with velocity pursuit guidance law at the ideal conditions and deduced an analytical expression. Normalizing the analytical expression, we obtained only one design parameter, non-dimentional termi?nal guided time, which can directly determine the guidance accuracy and the missile lateral accelera?tion. The scope of the parameter was given by analyzing non- dimensional lateral acceleration and miss- distance.
Key words
control ana navigation technology of aerocraft /
velocity pursuit guidance law /
guidance loop /
miss distance
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References
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Footnotes
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