反舰导弹对舰艇编队联合突防能力的研究

该文首先对单舰以及舰艇编队防御过程进行了分析,然后根据反舰导弹和舰空导弹武器的性能参数,提出了一种用于评估多型反舰导弹对舰艇编队联合突防能力的模型,最后计算并分析了仿真结果.     

防空导弹防御系统中的TBM突防能力研究

建立了防空导弹弹道数学模型并应用排队论理论建立了TBM突防概率模型。通过仿真计算，深入定量地探讨了TBM的进入密度、防御武器数量和火力单元拦截概率等因素对TBM突防能力的影响，在此基础上，从导弹技术与战术运用方面，针对防空导弹的防御，进一步提高TBM突防能力的对策和途径。     

新型反舰导弹对舰艇防御的挑战与对策

针对舰艇防御所面临的新挑战,围绕舰艇对新一代反舰导弹防御的对策问题,介绍了新一代反舰导弹发展的特点,并对舰艇如何建立有效的防御体系、提高预警能力、发展炮弹组合防空武器系统、增强对反舰导弹弹载设备的干扰、研制新概念武器等的技术途径作了简要介绍.     

飞航导弹对地空导弹的作战效能分析

根据美国工业界武器系统效能咨询委员会对作战效能的定义，针对某型飞航导弹给出了其作战交通分析模型的解析法表述，建立了飞航导弹与某典型地空导弹攻防对搞的仿真模型，最后对该模型进行了数学仿真验证，并分析了影响导弹作战效能的主要因素。结果表明，可以从降低飞航导弹的RCS值、采用超低空突防和多发齐射等三个方面提高飞航导弹对地空导弹的作战效能。     

导弹气动伺服弹性稳定性分析

分析了带有舵面及控制系统的战术导弹的气动伺服弹性稳定性。动力学方程中包含弹体的一阶弯曲振动、弹体的刚体平动和转动 ,可控舵面只考虑刚体偏转。用细长体理论和气动导数方法计算了导弹的非定常气动力 ,两种方法均适用于亚音速和超音速情况。采用 Nyquist方法和 Bode图方法分析了某导弹的气动伺服弹性稳定性和稳定裕度 ,两种气动力方法所得结果一致。     

战术导弹绕流流场并行计算

本文采用求解NS方程的方法对战术导弹的流场进行了数值模拟.应用区域分割技术和拼接网格的并行策略,发展了一种适合于分布式存贮并行环境的隐式有限体积并行算法,在PVM并行环境下,对战术导弹绕流流场实现了单块网格多机并行计算和多块网格多机并行计算,通过负载平衡等方法得到了较高的加速比.计算结果表明并行计算结果与串行计算结果完全一致.     

反舰导弹的隐身技术

通过对而向新世纪反舰导弹作战需求的分析,介绍了红外隐身技术和雷达隐身技术在反舰导弹中的应用,并指出隐身技术应用于反舰导弹需要解决的几个问题,为其发展提供参考.     

Space-based tactical ballistic missile launch parameter estimation

The author explores the influence of a priori uncertainties in launch time and trajectory fly-out profiles, along with sensor angle measurement errors, on the estimation of missile launch location and heading angle. An error model is developed to compute the statistics of the estimation errors using a single pair of angle measurements, one from each of two satellites, or both from the same satellite platform. The measurements and estimation methods are described, followed by a derivation of the estimation errors for the hypothetical case of perfect knowledge of trajectory and launch time. Using the ideal case as a framework, the errors are generalized to include trajectory and launch time uncertainties. The results are discussed with the aid of graphics which were run parametrically to highlight important dependencies and sensitivities     

A passive tracking filter for missile capture

A practical filter is suggested for ground-based missile tracking in a capture-guidance mode utilizing angle-only measurements from a passive missile sensor, and its performance is evaluated by a realistic system-simulation study. A missile-acceleration model that provides inputs to the filter is also suggested. The filter has a decoupled structure of independent azimuth and elevation channels, which requires fewer computations in solving the filter gain compared to a coupled structure. Simulation results show good tracking performance of the filter when used in association with the proposed missile-acceleration model     

反舰导弹捕捉危险区的计算方法

指出现有方法设定的捕捉危险区过大,给保障和警戒船只造成多余的负担,阐明了根据反舰导弹自控终点的分布特点,利用概率论的有关理论,推导并设计了一种适合具有自控+自导体制的各种类型反舰导弹捕捉危险区域的计算方法.该算法可简单、方便、准确地设定反舰导弹捕捉危险区域.     

Fuzzy gain-scheduled missile autopilot design using evolutionary algorithms

The paper presents the lateral acceleration control design of a missile model using the evolution strategy (ES). The nonlinear fixed-structure-like controller is represented by the singleton fuzzy model. This allows a variation of shapes of the gain functions to be explored, and subsequent modification is fairly easy. Instead of finding an optimal decomposition of the fuzzy controller, a set of fuzzy rules is unconventionally optimized for the overall gain surfaces that guarantee acceptable performances for the closed-loop system over the whole operating envelope. The simulation results show that the designed fuzzy gain-scheduled controller is a robust tracking controller for all perturbation vertices     

空面导弹弹道的舵面控制律设计

研究导弹在发射后飞行阶段的控制律。首先建立导弹总体布局数学模型和气动模型 ,再分别对导弹的纵向、横向和滚转向的控制律进行分析 ,其中纵向分为下滑段、巡航段和末段制导俯冲段 ,并依次对每一阶段的控制律进行分析 ,最后 ,对下滑段升降舵控制律进行算例计算。实际应用表明 ,所设计的控制律是正确的 ,能够保证导弹最终精确击中目标。     

导弹过载模型及控制器设计

将导弹的俯仰和偏航通道没计成耦合系统,滚转通道单独设计成稳定系统,以导弹的两个法向过载为状态变量,建立了导弹的非线性时变模型.在此基础上实现了反演控制器设计,并在控制量中引入了鲁棒控制项,改善了系统的控制效果.最后应用Lyapunov稳定性理论证明了系统是渐近稳定的.仿真结果说明了该设计方法的有效性和可行性.     

反辐射导弹及地面雷达的诱饵对抗技术

介绍了国外主要反辐射导弹的现状、性能以及它的发展趋势,针对反辐射导弹的缺点以及部队装备的现状提出了诱饵对抗技术,分析了诱饵抗反辐射导弹的工作原理,并提出了对雷达模拟伺服系统进行数字化改造实现同步控制.     

Genetic programming for anti-air missile proximity fuze delay-timealgorithms

This paper describes the application of genetic programming to delay-time algorithms for anti-air missiles equipped with proximity fuzes. Current algorithms for determining the delay-time before the detonation of a missile warhead rely on human effort and experience and are, in general, deficient. We show that by applying genetic programming, an evolutionary optimization technique, determination of the timing can be automated and made near-optimal. A simulation study is discussed     

一种导弹导引律及参数的非线性MMAE辨识方法

针对现代空战中来袭导弹导引律参数辨识问题,提出了一种非线性的多模型自适应(MMAE)辨识方法。采用无色卡尔曼滤波(UKF)方法对非线性多模型集进行状态估计。利用多模型自适应估计方法,设计了导弹的导引律及参数辨识器,在三维坐标内实现了对导弹IPN,APN,OGL和PP导引律及对应导引参数的辨识,并通过算例仿真验证了该方法的快速性和准确性。     

导弹拦截点计算及其仿真分析

导弹拦截点的计算对研究引信战斗部一体化设计和毁伤效果的分析及评价具有重要意义.以防空导弹和空空导弹广泛使用的破片式战斗部为例,建立了求解拦截点的数学模型,通过控制变量法用Madab软件分析研究了导弹拦截点的影响因素并得出为获得较理想拦截距离的相关参数要求.从而为导弹引信战斗部一体化设计和毁伤评估奠定了必要基础.     

Terminal attitude selection method of missile attack aircraft

The appropriate terminal attitude of missile is important to improve the damage effectiveness of fragmentation warhead against aircraft targets.In this paper,three missile terminal attitude selection methods are proposed to solve the problem of terminal attitude selection in different situations according to their respective evaluation indexes.The MVE-based method uses the damage probability of each detonation point around the aircraft at a given attitude of missile to calculate the Mean Volume of Effectiveness(MVE) at the corresponding attitude,and then uses the MVE for different attitudes to select the terminal strike attitude.The detonation position-based method addresses the case where the missile detonation position can be assessed in advance.Given the effects of missile guidance errors and fuze activation position errors,Monte Carlo simulations are used to calculate the damage probability of aircraft with different strike attitudes,from which the terminal strike attitude is selected.The BP-ANN model-based method uses the constructed Back Propagation Artificial Neural Network(BP-ANN) model instead of simulation to calculate the evaluation indexes in the corresponding cases of MVE-based method and Detonation position-based method,which can improve the efficiency of attitude selection.Simulations are conducted for different scenarios to verify the feasibility and effectiveness of the proposed method.     

基于UML的空空导弹仿真建模

采用统一建模语言对空空导弹仿真系统的建模过程进行了研究。通过用例图进行了空空导弹仿真系统的功能需求分析,采用包图和类图建立了空空导弹仿真系统的静态结构模型,给出了类包结构和类之间的继承和组合关系,对空空导弹仿真系统进行了功能分解。采用状态图建立了空空导弹生命期模型,给出了空空导弹从创建到销毁过程中的不同状态之间的转换关系。采用序列图对空空导弹发射后的动态行为进行了建模。最后采用C++语言对所建立的模型进行了仿真实现。