前言用于攻击空间大机动目标的空空导弹,一般采用鸭式布局。这种布局机动性好,可用过载高,但随之而来的问题是诱导滚动力矩大,因而给滚动控制系统设计带来一定困难。笔者参考已有的文献就几个具体型号作了实际计算研究,并进行了部分风洞试验,取得了满意的结果,对解决这一工程问题具有积极意义。本文仅对这一研究的部分内容予以介绍,供参考。我们知道,导弹攻击空间目标时,一般都是俯仰舵和偏航舵同时偏转,作复合控制,产 Foreword The air-to-air missiles that are used to attack large maneuvering targets in space generally use a canard layout. This layout has good maneuverability and high available overload, but the consequent problem is inducing a large rolling moment, which brings some difficulties to the design of the rolling control system. Based on the existing literature, the author made some practical calculation studies on several specific models and carried out some wind tunnel tests and achieved satisfactory results, which is of positive significance for solving this engineering problem. This article only describes some of the contents of this study for reference. We know that when a missile attacks a space target, pitch and yaw rudder are generally deflected at the same time for compound control