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.
针对大离轴发射条件下的近距格斗导弹，分析了大离轴制导的要求，提出了适用于大离轴制导阶段的快速转弯制导律，并进行了推导及分析。
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.
针对大离轴发射条件下的近距格斗导弹，分析了大离轴制导的要求，提出了适用于大离轴制导阶段的快速转弯制导律，并进行了推导及分析。
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