| 直接力与气动力复合控制拦截弹轨迹控制 |
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| 引用本文： | 尹永鑫,杨明,王松艳.直接力与气动力复合控制拦截弹轨迹控制[J].航空动力学报,2008,23(3):569-573. |
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| 作者姓名： | 尹永鑫 杨明 王松艳 |
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| 作者单位： | 哈尔滨工业大学,控制与仿真中心,哈尔滨,150001 |
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| 基金项目： | 国家自然科学基金(60434010)，黑龙江省杰出青年基金(JC200606) |
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| 摘 要： | 研究了直接力与气动力复合控制拦截弹的轨迹控制问题.建立了复合控制拦截弹的动力学模型,分析了不同复合方式的差别,指出了直接力对弹体运动的影响.建立了拦截弹与目标的相对运动模型,针对直接力与气动力复合控制的特殊性,基于滑模控制理论给出了轨迹控制算法,并在此基础上针对传统控制方法的缺陷,设计了脉冲发动机的点火逻辑.仿真结果表明,该方法能有效的实现拦截弹在末制导段的精确制导控制,并具有较强的鲁棒性.
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| 关 键 词： | 航空、航天推进系统 非线性控制系统 飞行轨迹 滑模制导律 拦截弹 |
| 文章编号： | 1000-8055(2008)03-0569-05 |
| 收稿时间： | 2007/3/16 0:00:00 |
| 修稿时间： | 2007年3月16日 |
Trajectory control for interceptor missile with combined control of lateral thrust and aerodynamics |
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| YIN Yong-xin,YANG Ming and WANG Song-yan.Trajectory control for interceptor missile with combined control of lateral thrust and aerodynamics[J].Journal of Aerospace Power,2008,23(3):569-573. |
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| Authors: | YIN Yong-xin YANG Ming and WANG Song-yan |
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| Affiliation: | Control and Simulation Center, Harbin Institute of Technology, Harbin 150001, China;Control and Simulation Center, Harbin Institute of Technology, Harbin 150001, China;Control and Simulation Center, Harbin Institute of Technology, Harbin 150001, China |
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| Abstract: | The ability of a trajectory control system to control an interceptor missile with combined control of lateral thrust and aerodynamics was investigated.A dynamical model for interceptor missile with combined control was established.After analyzing differences between various combinations of control for interceptor missiles,impacts of lateral thrust on the motion of interceptor missiles were presented.A model of relative movement between the target and interceptor missile was established.Addressing the particularities of combined control for interceptor missiles,a trajectory control algorithm was designed based on the sliding mode control theory.On the basis of which,fire logic was presented for pulse thrusters in order to improve limitation of simple control method.Simulation results show that this method can effectively implement precise guidance for interceptor missiles at the final guidance stage as well as providing preferable robust stability. |
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| Keywords: | aerospace propulsion system nonlinear control system trajectory sliding mode guidance interceptor missile |
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