| 弹-架间隙的非线性模拟与特性分析 |
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| 引用本文： | 朱怀亮.弹-架间隙的非线性模拟与特性分析[J].宇航学报,2002,23(3):56-60. |
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| 作者姓名： | 朱怀亮 |
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| 作者单位： | 上海大学力学系,上海,200436 |
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| 摘 要： | 以大长径比低速旋转火箭为例,探讨弹-架间隙非线性特性对不同发射装置系统的动力响应的影响,当飞行器以S个定心部沿发射装置滑移时,根据弹、架横向相对位移确定其定心部处接触刚度和支承特性,模拟弹-架间隙效应。分别就刚性和柔性两种发射装置,分析了间隙量、支承刚度和转速等因素对飞行器发射中的姿态和系统动力特性的影响,算例与实际情况的相吻合证明了该方法的有效性。
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| 关 键 词： | 非线性模拟 飞行器 动力学 发射特性 弹－架间隙 |
| 文章编号： | 1000-1328(2002)03-0056-05 |
| 修稿时间： | 2001年2月9日 |
Simulation and analysis of the nonlinear clearance characteristics between the missile and launcher |
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| ZHU Huai,liang.Simulation and analysis of the nonlinear clearance characteristics between the missile and launcher[J].Journal of Astronautics,2002,23(3):56-60. |
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| Authors: | ZHU Huai liang |
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| Abstract: | This paper takes a large slenderness ratio spin rocket with a low spin velocity for example,and the launch dynamic behavior of the system is investigated when there is a clearance between the missile and the launcher.The varying contact stiffness of the "shoe" of missile is determined based upon traverse relative deformation between the missile and launcher during launch phase.The influence of the clearness,spin rate and support stiffness on rocket's motion attitude and dynamic behavior of the system is studied.The numerical results show the good accuracy and reliability. |
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| Keywords: | Missile Dynamics Launch behavior a clearance between the missile and launcher |
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