Adaptive dynamic surface control for integrated missile guidance and autopilot

Integrated guidance and control for homing missiles utilizing adaptive dynamic surface control approach is considered based on the three channels independence design idea. A time-varying integrated guidance and control model with unmatched uncertainties is first formulated for the pitch channel, and an adaptive dynamic surface control algorithm is further developed to deal with these unmatched uncertainties. It is proved that the proposed feedback controller can ensure not only the accuracy of target interception, but also the stability of the missile dynamics. Then, the same control approach is further applied to the control design of the yaw and roll channels. The 6-degree-of-freedom (6-DOF) nonlinear missile simulation results demonstrate the feasibility and advantage of the proposed integrated guidance and control design scheme.     

基于OpenGL的反舰导弹弹道视景仿真

针对导弹仿真系统开发中建模复杂且重复度高的问题,采用OpenGL库建立复杂模型的方法绘制了导弹飞行仿真所需的场景图像,建立了可用于导出模型的动态链接库,在对反舰导弹弹道特点进行认真分析的基础上,基于弹道规划原理,在VC环境下开发了可满足实际性能要求的弹道可视化仿真系统平台。对系统提供了真实的三维场景,可将弹道仿真节点计算出来的弹道数据以三维可视化技术展示出来。实验证明系统灵活通用,可提供完整的视景演示,为有效规划导弹弹道提供了有效支持。     

基于地磁场扰动探测的巡航导弹定位系统设计

为了大范围探测、准确识别、精确定位巡航导弹,提出一种基于地磁场扰动探测的巡航导弹识别定位系统。根据毕奥—沙伐尔定律和电磁感应定律,设计了通过磁场扰动反演巡航导弹位置、距离等特征信息的方法,建立了相应的数学模型。通过仿真分析可知,磁场扰动强度主要取决于被测物与磁探测器的距离、被测物的尺寸以及被测物的速度。通过Matlab仿真,分别给出了3个参数与磁场扰动强度的函数关系图。实验采用金属柱等比例模拟巡航导弹飞行穿过恒磁场的物理过程,得到了不同距离、不同速度条件下被测金属柱产生的磁场扰动强度,从而反演被测物的特征信息。实验证明其原理可行,探测范围和精度可以根据具体要求调节。     

Stealth Considerations for Aerodynamic Configurations Design of Missiles

The aerodynamic design of a strategic weapon is of interest, especially when the radar signatures are included in the conceptual design phase. The basics of stealth configurations and stealth mechanisms for missiles are reviewed. The Radar Cross Sections (RCS) of some generic missiles are predicted and compared to analyze the trade-offs involved between low RCS and aerodynamic performance. The consideration of RCS prediction in the conceptual design phase gives a quick insight into the stealth performance p...     

Coning motion stability and decoupling methods analysis of spinning missiles with angle-of-attack feedback autopilot

The angle-of-attack (AOA) three-loop feedback autopilot is an improved three-loop autopilot that has been widely employed in missile control systems. For spinning missiles, however, unstable coning motion can be induced by the cross-couple effect. For spinning missiles with an AOA feedback autopilot, this paper analyzes the coning motion stability with the consideration of the augmentation loop and the position of the accelerometer and compares the performance of three decoupling methods. First, a novel double-channel actuator AOA three-loop autopilot is established, and the sufficient and necessary condition of coning motion stability is proposed analytically on account of the complex system equations. The stability condition shows that the stable region of the design parameters for the autopilot shrinks as a result of the spinning condition. Moreover, methods associated with actuator dynamics, control coupling, static stability, and the decoupling method of setting the lead angle to the control system are presented to improve the stability of spinning missiles. Numerical simulations are implemented to demonstrate the accuracy of the proposed methods, whose results illustrate that the stability conditions can guide AOA autopilot design for the flight stabilization of spinning missiles.     

反舰导弹攻击战术的超视距跨跃

反舰导弹攻击战术的超视距跨跃，是反舰导弹在装备技术、战术思想、射击与攻击指挥、战术决策和战法、训法等方面的全面变革。结合未来反舰导弹技术发展趋势和海战场特点，重点分析和论述了未来反舰导弹在作战样式、射击方式、射击距离判别、火分目标选择、攻击形态、攻击方式、攻击模式、指挥方式、战术决策指导思想、决策内容和决策方法等方面的发展与变革。     

旋转导弹喷气阻尼效应建模与分析

旋转导弹在主动段不仅受到气动力和气动力矩的作用,还受到质量特性变化和喷气的影响。为研究旋转导弹在主动段的运动特性,对其喷气阻尼效应进行了建模与分析。首先,将旋转导弹看作连续质点系,根据变质量力学的基本原理,建立了同时考虑气动力矩、喷气阻尼效应和变质量特性的旋转导弹动力学方程;然后,分别对喷气阻尼效应和非线性变质量特性作用下导弹自旋转速和锥形运动的特性进行了理论分析,推导了喷气阻尼效应和气动力矩共同作用下旋转速度的表达式,并分析了锥形运动的稳定性,得到了稳定的充要条件;最后,利用数值仿真对理论分析的结果进行了验证.理论分析和仿真结果表明:喷气阻尼效应和变质量特性会影响导弹的自旋转速和锥形运动特性;若要保持导弹转速不变,应使药柱半径略小于发动机喷口截面半径,而喷气阻尼效应增大了锥形运动的阻尼,有利于保持锥形运动的稳定;质量特性的非线性变化能使锥形运动更快收敛;喷气阻尼效应和变质量特性对旋转导弹运动特性的影响不可忽略,在设计和分析中应加以考虑.     

非线性滤波在组合导航中的应用研究

组合导航系统是现代导航设备的一个主要发展方向,在人类航空、航天等领域被广泛运用.实现高精度、高可靠性、高抗干扰性是任何一种单一的导航系统都难以胜任的.组合导航系统通常以SINS为主导航系统,将GPS等导航定位误差不随时间积累的导航系统作为辅助导航系统,应用传感器信息融合技术和滤波技术,对组合系统的状态变量进行估计,从而给出高精度的导航参数.     

中段飞行弹道导弹表面温度与辐射特性计算

中段飞行弹道导弹目标辐射特性对于探测手段选择、传感器设计等具有重要意义.以采用红外隐身技术的弹道导弹为研究对象,考虑表面隐身涂层特性和进出地影的影响,采用有限体积法计算了弹道导弹在整个中段飞行过程中的温度变化;结合导弹自身辐射与太阳、地球辐射光谱,给出了导弹0～15μm范围内的辐射特性;研究了导弹表面温度和辐射特性的关...     

瞬态激励下圆盘轴向电磁能量的流动规律

本文给出了在瞬态均匀电流分布激励下,圆盘轴线上能量衰减的精确解。当激励波形选为矩形脉冲,且 a/c 时,在靠近源的区域内存在一个能量上升阶段,在达到最大值之后能量开始慢衰减,到无穷远处时即成为球面波衰减;无衰减区域是不存在的;能量上升阶段的范围决定于天线的尺寸以及脉冲的宽度。文中还给出了单频信号激励下,轴线附近的功率流线管。单频解表明:在靠近源的区域内存在一振荡区域,其幅度呈上升趋势,与Silver在1949年得出的结论不同。最后对时域能最上升段进行了解释,并对电磁导弹的一些问题进行了讨论。