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为了对付低空飞行的目标,目前有许多种超低空的防空导弹。一般导弹装在发射筒内,单人肩扛发射。射手把发射简扛在肩上,站着或跪着从肩上发射导弹。弹上装有红外线导引头和自动驾驶仪,按比例导引法控制导弹飞行。在目标能见度的条件下,以尾追或迎攻的方式攻击低空飞行的各种飞机。许多低空防空导弹只有一对舵而,因此是单通道控制。为了实现用一对舵面控制导弹的空间运动,导弹必须绕其纵轴低速旋转,这是单通道控制系统的一个特点。目前还缺乏这方面的分析资料,本文对单通道控制系统导弹控制力的产生进行初步分析,对导弹的旋转运动方程进行数学模拟,最后对大迴路进行了初步的模拟分析。
In order to deal with the goal of low-altitude flight, there are currently many kinds of ultra-low-altitude air defense missiles. General missile mounted in the launch tube, single shoulder launch. The shooter carried the launch paddle on his shoulder, standing or kneeling and firing missiles on his shoulder. The missile is equipped with infrared seeker and autopilot, guided by the proportion of guided missiles. Under the conditions of target visibility, all kinds of aircraft flying at low altitude are attacked by means of tail-chasing or attacking. Many low-altitude anti-aircraft missiles have only one pair of rudders and therefore are single-channel controls. In order to control the missile’s space motion with a pair of rudder surfaces, the missile must rotate at low speed about its longitudinal axis, which is a characteristic of a single-channel control system. At present, there is still a lack of analysis data in this aspect. This paper conducts a preliminary analysis on the generation of missile control force of a single-channel control system, and mathematically simulates the missile’s rotational motion equation. Finally, a preliminary simulation analysis of a large circuit is carried out.