三片转向翼旋转导弹的控制方法

2021 IEEE 4th Advanced Information Management, Communicates, Electronic and Automation Control Conference (IMCEC) Pub Date : 2021-06-18 DOI:10.1109/IMCEC51613.2021.9482101

Juanzhi Lu, Feng Wang, Jun Ma, Zhiqiang Yan, Lin Liu

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引用次数: 0

摘要

由于结构、重量等因素的限制，不能采用4片转向翼双通道控制一枚旋转导弹，低速时采用2片转向翼单通道控制效果也不理想。针对这种情况，提出了一种三片转向翼的控制方法。本文定义了准体系统下转向翼的安装位置和角度的极性，详细描述了三片转向翼的控制原理、控制指令的分配、控制力和力矩的计算。通过数学仿真验证了该方法的合理性和有效性。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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The control method for rotating missile with three pieces of steering wings

Due to the limitation of structure, weight and other factors, one rotating missile cannot be controlled by double channels of four pieces of steering wings, and the control effect with the single channel of two pieces of steering wings is dissatisfactory at low speed. In this case, a control method with three pieces of steering wings is proposed. In this paper, the mounting position of the steering wings and the polarity of the angle are defined under the quasi-body system, the control principle of three pieces of steering wings, the control command distribution, the calculation of control force and moment are described in detail. the rationality and validity of the method has been verified by mathematical simulation.

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来源期刊

2021 IEEE 4th Advanced Information Management, Communicates, Electronic and Automation Control Conference (IMCEC)

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