| 采用摆动喷管推力矢量控制弹性弹体数学模型建立 |
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| 引用本文： | 郑勇斌,林丽. 采用摆动喷管推力矢量控制弹性弹体数学模型建立[J]. 现代防御技术, 2007, 35(1): 41-44 |
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| 作者姓名： | 郑勇斌 林丽 |
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| 作者单位： | 中国航天科工集团公司,二院二部,北京,100854 |
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| 摘 要： | 针对摆动喷管不同于空气舵的特征,建立了摆动喷管坐标系,具体分析了单个摆动喷管产生的力和力矩,详细推导了采用摆动喷管推力矢量控制弹体弹性振动方程;同时基于小偏差线性化条件,推导了俯仰通道的姿态运动方程;以上方程可用于采用摆动喷管推力矢量控制弹体弹性计算和控制系统进一步设计的依据。
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| 关 键 词： | 摆动喷管 弹性振动 小偏差线性化 俯仰通道 |
| 文章编号： | 1009-086X(2007)01-0041-04 |
| 修稿时间： | 2006-06-15 |
Mathematical Model of Elasticity Missiles with Swing Nozzle Thrust Vector Control |
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| ZHENG Yong-bin,LIN li. Mathematical Model of Elasticity Missiles with Swing Nozzle Thrust Vector Control[J]. Modern Defence Technology, 2007, 35(1): 41-44 |
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| Authors: | ZHENG Yong-bin LIN li |
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| Abstract: | According to the characteristic of swing nozzle different from aero-fin,coordinates of swing nozzle is established.Force and torque of single nozzle are analyzed.Elasticity vibration formula with nozzle thrust vector control are derived.Based on the condition of small error linearization,attitude motion formula on pitch plane of missiles are educed.The formula can be used as the credential on the calculation of missiles elasticity and further design of control system. |
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| Keywords: | swing nozzle elasticity vibration mini-derivative linearization pitch loop |
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