影响动力平衡角的诸因素及其对弹道轨迹的影响

本文利用简化的刚体弹道方程分析了各种空气动力系数对于动力平衡角的大小及其曲线形状的影响,并在此基础上论述了动力平衡角对于射程及偏流的影响。通过计算表明,由动力平衡角产生的马格努斯力有时对射程会产生较大的影响。此外由马格努斯力矩等因素造成的动力平衡角曲线形状的变化,在某些情况下通过升力对射程也会产生较大的影响。     

柴油喷雾碰壁特性的模拟计算

提出一个柴油喷雾碰壁的数学模型,计算分析了垂直碰壁和倾斜碰壁时虽面射流的传播和混合特性.建立了新的壁面射流贯穿距离计算公式,结果显示这种计算方法是分析柴油喷注碰壁性能的简单而实用的工具.     

某型导弹弹翼静力分析的一种数学模型

应用有限元方法,建立了变厚度薄板三角形单元刚度矩阵,给出了变厚度薄板三角形单元形心上的应力和位移计算的数学模型。通过对某型反坦克导弹弹翼进行静力分析和实验比较,表明采用这种模型进行分析合乎结构设计精度要求。     

嵌银丝贫氧推进剂燃烧特性

采用试验发动机法 ,对嵌银丝铝镁贫氧推进剂的燃烧特性进行了研究 ,得到了低压下嵌银丝铝镁贫氧推进剂的燃烧规律 ,研究了银丝直径和贫氧推进剂配方对嵌银丝发动机燃速的影响。结果表明 ,嵌银丝贫氧推进剂的燃烧过程由初始工作段、稳定工作段和结束段组成 ;采用较粗的银丝 (0 3mm和0 4mm)可以显著提高贫氧推进剂的燃速 ;提高贫氧推进剂的基础燃速也是提高嵌银丝贫氧推进剂燃速的有效方法之一。     

基于MAS的末端防御网络化作战系统指控网

在简要介绍末端防御防空导弹网络化作战系统的基础上,分析了其指控网的结构和功能,并利用多智能体系统中的BD I模型对指控网的单个智能体进行描述,并重点研究了基于BD I结构的智能体的环境感知模型、作战意图模型、决策模型和通讯行为。     

目标反射特性对激光末制导精度的影响

从物理光学和辐射原理的角度分析了目标反射特性对激光末制导精度的影响 ,给出了目标反射系数的直接测量方法 ,最后得出结论并提出了减少受其影响的措施。分析结果表明目标反射特性会影响激光末制导炮弹的接收反射激光信号功率的大小 ,进而影响激光末制导炮弹的制导概率 ,因而对于不同质地的目标 ,要根据目标的反射系数来确定激光指示器可靠的照射距离 ,选择其照射攻击部位 ,以提高激光末制导精度。     

Optimal search for a moving target with the option to wait

We investigate the problem in which an agent has to find an object that moves between two locations according to a discrete Markov process (Pollock, Operat Res 18 (1970) 883–903). At every period, the agent has three options: searching left, searching right, and waiting. We assume that waiting is costless whereas searching is costly. Moreover, when the agent searches the location that contains the object, he finds it with probability 1 (i.e. there is no overlooking). Waiting can be useful because it could induce a more favorable probability distribution over the two locations next period. We find an essentially unique (nearly) optimal strategy, and prove that it is characterized by two thresholds (as conjectured by Weber, J Appl Probab 23 (1986) 708–717). We show, moreover, that it can never be optimal to search the location with the lower probability of containing the object. The latter result is far from obvious and is in clear contrast with the example in Ross (1983) for the model without waiting. © 2009 Wiley Periodicals, Inc. Naval Research Logistics 2009     

Strain concentration caused by the closed end contributes to cartridge case failure at the bottom

Ruptures at the bottom of cartridges are a common cause of failure of ammunitions, which directly threatens the safety of weapons and shooters. Based on plastic tube theory, this study analyses the radial and axial deformation of a cartridge, considering the radial constraint of the closed end at the bottom of the cartridge. Owing to the influence of the closed end, the bottom of a cartridge does not establish complete contact with the chamber. Owing to strain concentration in the non-contact area, this area is more amenable to the occurrence of cartridge rupture. This theory predicts the location of the fracture more accurately than the traditional theory. The maximum axial deformation of a cartridge comprises bending and friction deformation. The maximum strain at the bottom of the cartridge increased by 135% owing to the introduction of bending strain caused by the closed end. The strain distribution of a cartridge was measured using digital image correlation technology, and the measured result was consistent with the predicted results of the bending deformation theory and rupture case. The effects of wall thickness, radial clearance, friction coefficient, and axial clearance on the axial deformation of the cylinder were studied. Increasing the wall thickness and reducing radial clearance were found to reduce bending deformation; furthermore, lubrication and reduction in axial clearance reduce frictional deformation, which in turn reduce cartridge rupture.     

基于先验信息的分布式星载单基线SAR/ATI方法

在综述了分布式星载SAP/ATI技术的基础上,阐述了单基线SAP/ATI技术的原理和杂波、噪声对检测、测速性能的影响,给出了一种基于先验信息的单基线SAR/ATI检测和测速方法,最后基于多功能的天基雷达仿真系统进行了仿真实验和性能分析.     

无人机滑跑航迹控制模型与控制精度分析

航迹偏差的控制精度对滑跑起降至关重要,地面滑跑纠偏建模和地空航迹控制的切换策略是起降航迹控制设计的难点。从运动学关系出发,提出了地面滑跑纠偏控制的设计模型,使得复杂的地面航偏控制规律易于设计;利用同-反馈结构在多个状态的协调控制,实现了地空状态自然过渡的航迹控制切换策略;最后提出了提高航迹控制精度和进行风干扰补偿的措施。