导轨式机载导弹发射动力学模型及影响因素分析研究

廖莎莎; 吴成; 段继

doi:10.15892/j.cnki.djzdxb.2013.03.049

2013 , Vol. 33 >Issue 3: 153 - 156,162

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2013.03.049

摘要

针对导轨式机载导弹发射过程的特点,建立了包含发射倾角、滑轨长度、发动机推力偏心和随机风扰动等因素的动力学数学模型,并对其影响规律进行了分析;基于仿真计算,获得了在不同随机干扰因素下导弹的离轨运动规律和离轨参数。仿真结果对机载导弹导轨式发射系统设计提供工程计算的理论依据。

关键词： 机载导弹; 发射动力学; 推力偏心; 风扰动

本文引用格式

廖莎莎 , 吴成 , 段继 . 导轨式机载导弹发射动力学模型及影响因素分析研究[J]. 弹箭与制导学报, 2013 , 33(3) : 153 -156,162 . DOI: 10.15892/j.cnki.djzdxb.2013.03.049

Abstract

According to the characteristics of oriented-rail launch technique for airborne missile, launch dynamics and kinematics models were established. Some influence factors were analyzed, including pneumatic force, launch obliquity, slide length, thrust misalignment and stochastic wind disturbance. Based on simulation and calculation for airborne missile launch system, movement parameters and laws of the missile away slide were obtained. The simulation conclusion accords with practices, providing theory basis for oriented-rail launch system design.

Key words： airborne missile; launch dynamics; thrust misalignment; wind disturbance model

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参考文献

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