基于ANFIS的空袭目标攻击意图量化方法

为准确评估空袭目标的威胁程度和提高指挥员的防空决策水平,采用自适应神经模糊推理系统(ANFIS)对空袭目标的攻击意图量化分析。该方法将模糊推理和人工神经网络有机地结合起来,充分利用专家知识,综合集成了航向角攻击意图系数和高度攻击意图系数。仿真结果表明,建立的攻击意图量化系统反映了影响因素和攻击意图的映射规律,方法合理有效,能够为防空作战提供决策支持。     

低入射余角下雷达地杂波反射率模型

在常用雷达地杂波反射率模型的基础上,综合考虑雷达频率、地形种类和入射余角等对地杂波反射率的影响,建立了一个低入射余角下雷达地杂波反射率模型,并在不同的情况下,该模型与其他常用地杂波反射率模型相比较。结果表明:该雷达地杂波反射率模型更符合实际,进而证明了该模型的有效性和实用性。     

区间正交小波变换域FLP算法及其在捷联寻北中的应用

针对机抖激光陀螺角随机游走和发动机干扰等影响静态捷联寻北精度的问题,提出了一种新的基于区间正交小波变换的前向线性预测算法。该算法利用前向线性预测技术以及区间正交小波变换抑制边界效应的能力,有效地减小了角随机游走和发动机干扰。车载实验证明该算法的有效性。     

Effect of change of sand properties on travel distance of ricocheted debris

The debris from exploded buildings can ricochet after colliding with the ground, thus increasing the debris travel distance and danger from any associated impacts or collisions. To reduce this danger, the travel distance of ricocheted debris must be accurately predicted. This study analyzed the change in the travel distance of ricocheted concrete debris relative to changes in the properties of a sand medium. Direct shear tests were conducted to measure the change in internal friction angle as a function of temperature and water content of the sand. Finite element analysis (FEA) was then applied to these variables to predict the speed and angle of the debris after ricochet. The FEA results were compared with results of low-speed ricochet experiments, which employed variable temperature and water content. The travel distance of the debris was calculated using MATLAB, via trajectory equations considering the drag coefficient. As the internal friction angle decreased, the shear stress decreased, leading to deeper penetration of the debris into the sand. As the loss of kinetic energy increased, the velocity and travel distance of the ricocheted debris decreased. Changes in the ricochet velocity and travel distance of the debris, according to changes in the internal friction angle, indicated that the debris was affected by the environment.     

Numerical investigation on free air blast loads generated from center-initiated cylindrical charges with varied aspect ratio in arbitrary orientation

In current guidelines, the free air blast loads (overpressure and impulse) are determined by spherical charges, although most of ordnance devices are more nearly cylindrical than spherical in geometry. This may result in a great underestimation of blast loads in the near field and lead to an unsafe design. However, there is still a lack of systematic quantitative analysis of the blast loads generated from cylindrical charges. In this study, a numerical model is developed by using the hydrocode AUTODYN to investigate the influences of aspect ratio and orientation on the free air blast loads generated from center-initiated cylindrical charges. This is done by examining the pressure contours, the peak overpressures and impulses for various aspect ratios ranged from 1 to 8 and arbitrary orientation monitored along every azimuth angle with an interval of 5°. To characterize the distribution patterns of blast loads, three regions, i.e., the axial region, the vertex region and the radial region are identified, and the propagation of blast waves in each region is analyzed in detail. The complexity of blast loads of cylindrical charges is found to result from the bridge wave and its interaction with primary waves. Several empirical formulas are presented based on curve-fitting the numerical data, including the orientation where the maximum peak overpressure emerges, the critical scaled distance beyond which the charge shape effect could be neglected and blast loads with varied aspect ratio in arbitrary orientation, all of which are useful for blast-resistant design.     

角度欺骗有源假目标的动力学特性

针对高空高速目标探测过程中可能出现的角度类欺骗有源假目标,从理论上系统地分析了其动力学性质,导出了假目标的动力学方程,并分析了假目标的机械能和动量矩守恒问题。理论分析和仿真试验均表明,具有固定角度欺骗的方位有源假目标其动力学特性和真实目标完全一致,在动力学上是无法鉴别真伪的;除此之外的其他角度类欺骗有源假目标均不满足高空高速目标椭圆轨道特性以及动力学守恒定律,利用这种差异可以在数据处理层对假目标进行鉴别。     

基于滑移网格的潜艇旋臂试验数值模拟?

潜艇水动力系数对潜艇操纵性研究具有重要意义。为了获取较高精度的潜艇旋转导数,以分区结构化网格为基础,采用基于固定坐标系的滑移网格方法,对SUBOFF潜艇进行旋臂试验数值仿真。并对比两种不同的湍流模型下仿真结果,误差均在8％以内,满足工程要求,验证了方法的可行性。     

尾流自导鱼雷直进射击系统误差的提前角修正方法

针对尾流自导鱼雷直进射击方式下弹道简化产生的命中结果系统误差问题,采用几何分析法,首先,分析了尾流自导鱼雷的直进射击原理;然后,依据尾流自导鱼雷弹道过程,建立了尾流自导鱼雷命中点偏差的解析计算模型,并分析了该偏差对鱼雷命中效果的影响;最后,研究了消除该系统误差的提前角修正方法。通过实例论证了该修正方法的可行性和有效性。     

便携式自寻的反坦克导弹攻顶弹道研究

便携式反坦克导弹在通过击顶方式打击目标时,要同时满足落角和精度的要求,以达到对目标的毁伤效能。首先推导带落角约束的最优比例导引律;然后设计携式反坦克导弹击顶弹道方案,导弹先出筒无控,以指数规律完成爬升,采用定攻角进行滑翔飞行,弹道末端运用推导的导引律来满足对落点和落角的约束。仿真结果表明,当反坦克导弹攻击不同距离的目标时,该弹道方案具有较强的有效性。     

机械抖动偏频激光陀螺静态测角方法

阐述采用机械抖动偏频激光陀螺进行静态角度测量的原理,分析测角随机误差与激光陀螺角随机游走系数、测量时间的关系,通过转台分度误差实验验证了测角随机误差公式。采用排列互比法对测角系统误差和转台分度误差进行分离。实验与理论分析表明,静态测角方法具有良好的环境适应性和稳定性,测角随机误差优于0.26″,系统误差优于1″。最后分析了进一步减小测角随机误差和系统误差的措施。