动力调谐陀螺随机速率漂移模型及其分析

应用典型相关分析,主成份分析和多因变量逐步回归分析方法,对陀螺仅随机速率漂移与温度的关系数推进行了分析。文中得出了一些有益的结论,并建立了陀螺仪随机速率漂移与温度相关的数学模型。     

机器人步行腿机构的动力分析

本文根据力的叠加原理,采用拆杆拆副法,对一平面闭式多杆步行腿机构进行了较为全面的动力分析,得出了一个运动循环内原动曲柄的输入力矩及各运动副处的约束反力线图,为该机构的驱动、控制及进一步的改型设计提供了必不可少的计算依据。线图分析表明:该机构节省能量,力学性能较好,有良好的应用前景。     

多目标决策的特殊坐标系求解方法

在多目标决策问题中,满意解常常要在非劣解中寻找。一般来讲,对于两个目标(二维)的解的判别并不困难,但遇到多个目标(n维),且有多个可行解时,对非劣解的判别就显得有些繁复了。因此,采用直观容易的特殊坐标系来判别"非劣解",从而给出求解多目标决策问题满意解的方法。     

用于无线ATM的协议及方法分析

ＷＡＴＭ 被认为是下一代个人通信网络的解决方案,或是Ｂ－ＩＳＤＮ 网络的无线延伸。目前无线ＡＴＭ 仍处于发展初期,ＡＴＭ 论坛和ＩＴＵ－Ｔ 都未制定正式标准,研究人员正在建立实验性的Ｗ ＡＴＭ 网络,并在其上面实验各种不同的协议。ＡＴＭ 类的无线网络将在未来的宽带通信网中扮演一个重要的角色     

一种不需要特征值分解的MUSIC方法

MUSIC方法是空间谱估计中经典的子空间方法。提出了一种构造参考信号的预处理模型,提出了一种适合于MUSIC方法的多级维纳滤波结构。新方法避免了采样数据二阶统计的特征值分解,降低了运算量。仿真结果证明了方法的有效性。     

弹道导弹防御中多目标拦截的策略

多目标拦截是弹道导弹防御的重大难题,也是目前美国导弹防御系统所遇到的最大的技术难点。在将多目标问题分为单弹头攻击和多弹头攻击2类问题的基础上,结合美国的相关研究计划,分别针对核爆炸防御、助推段防御、先进的目标识别器和多拦截器防御等多目标拦截策略进行了分析研究。     

The minmax multidimensional knapsack problem with application to a chance‐constrained problem

In this paper we present a new combinatorial problem, called minmax multidimensional knapsack problem (MKP), motivated by a military logistics problem. The logistics problem is a two‐period, two‐level, chance‐constrained problem with recourse. We show that the MKP is NP‐hard and develop a practically efficient combinatorial algorithm for solving it. We also show that under some reasonable assumptions regarding the operational setting of the logistics problem, the chance‐constrained optimization problem is decomposable into a series of MKPs that are solved separately. © 2007 Wiley Periodicals, Inc. Naval Research Logistics, 2007     

Parallel machine scheduling with eligibility constraints: A composite dispatching rule to minimize total weighted tardiness

We study a parallel machine scheduling problem, where a job j can only be processed on a specific subset of machines M_j, and the M_j subsets of the n jobs are nested. We develop a two‐phase heuristic for minimizing the total weighted tardiness subject to the machine eligibility constraints. In the first phase, we compute the factors and statistics that characterize a problem instance. In the second phase, we propose a new composite dispatching rule, the Apparent Tardiness Cost with Flexibility considerations (ATCF) rule, which is governed by several scaling parameters of which the values are determined by the factors obtained in the first phase. The ATCF rule is a generalization of the well‐known ATC rule which is very widely used in practice. We further discuss how to improve the dispatching rule using some simple but powerful properties without requiring additional computation time, and the improvement is quite satisfactory. We apply the Sequential Uniform Design Method to design our experiments and conduct an extensive computational study, and we perform tests on the performance of the ATCF rule using a real data set from a large hospital in China. We further compare its performance with that of the classical ATC rule. We also compare the schedules improved by the ATCF rule with what we believe are Near Optimal schedules generated by a general search procedure. The computational results show that especially with a low due date tightness, the ATCF rule performs significantly better than the well‐known ATC rule generating much improved schedules that are close to the Near Optimal schedules. © 2017 Wiley Periodicals, Inc. Naval Research Logistics 64: 249–267, 2017     

带三维落角约束的寻的导弹制导与姿控系统设计

针对带三维落角约束的寻的导弹制导与姿态控制系统设计问题,提出一种基于终端滑模控制和扩张状态观测器的六自由度制导控制系统设计方法。建立包含模型不确定项的寻的导弹六自由度质心与绕质心模型,设计内外双层环路六自由度制导控制系统框架;基于弹-目三维相对运动模型和坐标系转移矩阵建立以攻角和侧滑角为输入的三维全耦合导引方程,利用终端滑模控制方法和扩展状态观测器得到期望的攻角和侧滑角并将其转化为对应的俯仰、偏航和滚转角指令;根据线性形式的寻的导弹绕质心动力学方程,设计与俯仰、偏航和滚转角相关的滑模面向量,并利用终端滑模控制方法和扩张状态观测器得到寻的导弹的副翼偏角、方向舵偏角和俯仰舵偏角指令。六自由度数值仿真结果验证了该方法的有效性和鲁棒性,并证明了该制导控制系统设计方法能以较少的控制设计参数完成预设的制导控制任务。     

平流层飞艇抗风场干扰约束Unscented卡尔曼滤波算法设计与应用

为了提高风场干扰环境下飞艇的导航精度,研究飞艇抗风场干扰导航算法。在建立风场干扰条件下飞艇速度误差约束模型的基础上,设计抗风场干扰的约束Unscented卡尔曼滤波算法。确定风场干扰条件下飞艇的速度误差约束量,将该约束与Unscented卡尔曼滤波算法相结合,对速度误差进行估计和补偿,以减小风场对飞艇定位精度的影响;证明该算法的状态估计量不仅是无偏的,而且协方差小于标准Unscented卡尔曼滤波的协方差;将提出的算法应用于捷联惯导/天文/合成孔径雷达组合导航系统中进行仿真验证,并与自适应扩展卡尔曼滤波和抗差自适应Unscented卡尔曼滤波算法进行比较。结果表明:提出的约束Unscented卡尔曼滤波算法的滤波性能明显优于自适应扩展卡尔曼滤波和抗差自适应Unscented卡尔曼滤波算法,能够有效抑制风场对飞艇定位精度的影响,提高飞艇的导航定位精度。