| 大气层内燃气动力与气动力复合控制方法探讨 |
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| 引用本文： | 魏明英.大气层内燃气动力与气动力复合控制方法探讨[J].现代防御技术,2006,34(1):24-28. |
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| 作者姓名： | 魏明英 |
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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： | 对采用燃气动力(直接力)与气动力复合控制技术的控制方式、姿控发动机控制周期、点火逻辑及姿控发动机启控策略等进行了初步探讨。重点对采用燃气动力/气动力复合控制方式中舵系统的工作模式进行了探讨及仿真研究,对姿控发动机控制周期及控制回路工作周期对制导精度的影响进行了初步仿真研究。通过仿真研究表明:在末制导阶段,采用燃气动力/气动力复合控制方式可提高导弹的快速性,进而提高导弹的制导控制精度。
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| 关 键 词： | 燃气动力与气动力复合控制 点火逻辑 姿控发动机控制周期 |
| 文章编号： | 1009-086X(2006)01-0024-05 |
| 修稿时间： | 2005年9月26日 |
Research on control method of side jet and aerodynamic compound control in endoatmospheric |
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| WEI Ming-ying.Research on control method of side jet and aerodynamic compound control in endoatmospheric[J].Modern Defence Technology,2006,34(1):24-28. |
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| Authors: | WEI Ming-ying |
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| Abstract: | The control method of side jet and aerodynamic compound control,including side jet and aerodynamic compound control manner,control cycle of attitude control engine,ignition logic,startup control game of attitude control engine,etc.was researched.The work module of rudder was discussed and studied by simulation in side jet and aerodynamic compound control manner,the effect on guidance accuracy by control cycle of attitude control engine and action cycle of control loop was simulated.Simulation result showed that response time of missile was reduced and guidance accuracy was accordingly increased by side jet and aerodynamic compound control manner in terminal guidance. |
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| Keywords: | Side jet and aerodynamic compound control Ignition logic Control cycle of attitude control engine |
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