公开(公告)号：US3905563A

公开(公告)日：1975-09-16

申请号：US35438673

申请日：1973-04-25

Applicant: FUJI HEAVY IND LTD

Inventor： NAGOSHI SABURO

IPC: F41G7/22 ,  F41G7/34 ,  G05D1/12 ,  F42B15/02 ,  F41G7/00

CPC classification number: F41G7/22 ,  F41G7/224 ,  F41G7/34 ,  G05D1/12

Abstract: A system for controlling a missile motion in the homing mode comprises means for designating by an error signal a direction in which a missile is guided in the homing mode, and means for compounding with the error signal a predetermined biasing signal imparting acceleration in one or two dimensions normal to a direction of the missile derivation. The biasing signal causes shells from anti-aircraft guns and anti-missile missiles to increase the miss-distance to the missile, within the allowable maneuverability of the missile, whereby the missile evades defensive action and finally zeroes in on a target.

Abstract translation: 用于在归位模式中控制导弹运动的系统包括用于通过误差信号指定导弹在归位模式中被引导的方向的装置，以及用于与误差信号混合的预定偏置信号给予一个或两个加速度的装置 尺寸与导弹推导方向相符。 在弹道导弹的允许机动性范围内，偏置信号会导致高射炮和反导弹的炮弹增加与导弹的错过距离，导弹逃避防御作用，最终在目标上归零。