零阶保持器数字补偿在高炮跟踪系统中的应用

以某自行高炮跟踪系统为研究对象,通过对其跟踪系统数字校正环节的改进,对火控系统中A/D转换接口的零阶保持器进行了补偿.仿真结果表明,采用该方法后该系统的数字校正环节更好的保持了原设计时的控制特性,提高了跟踪精度,更有利于保持系统的总体最优性.     

某自行高炮跟踪模拟训练系统的设计与实现

采用模拟训练装置进行武器装备操作技能的训练已成为当今装备操作训练的重要发展趋势.介绍了某自行高炮跟踪模拟训练系统的设计要求,硬件组成和各软件模块的设计与实现.经部队实际测试表明,该系统能够解决目标航路的实时生成、控制、测量和显示等关键问题,实现对目标的搜索与跟踪训练.     

提高某自行高炮电视自动跟踪精度的方法研究

介绍了某自行高炮电视自动跟踪系统的分布式计算机控制结构 ,分析了系统产生误差的主要原因 ,并针对这种原因提出了对系统进行改进的方法。实验证明 ,这些方法的采用对于提高电视自动跟踪系统的跟踪精度和跟踪平稳性具有明显的作用。     

基于船载高炮武器平台的一种火控稳定技术

为提高船载高炮射击的精度,必须消除船体晃动对武器系统瞄准线和射击线的影响.以某牵引式高炮武器系统为研究对象,提出了一种火控稳定技术实现方案,并给出了相应的数据处理模型.     

自行高炮模拟仿真实验平台设计与实现

自行高炮模拟仿真实验平台可应用于火控原理教学和装备科研等场合。该实验平台以某型高炮构建解算模型,采用实物和半实物仿真的方法,以实际车体模型为运动载体,集成了导航、姿态测量系统、目标探测系统和武器系统的实体模型,在仿真火控计算机的控制下,可实现目标搜索、截获、电视自动跟踪、目标运动参数求取和射击诸元计算与输出等功能,同时,可处理车体姿态信息,实现瞄准线和武器线的稳定。该平台运动载体可以自动驾驶或遥控驾驶,配合仿真道路模拟车体姿态的变化,可以仿真短停射击和行进间射击等战术动作。     

火控文摘

为满足试验高炮防空系统全天候火控仪器的要求,研制了采用视频相关和形心跟踪技术的瞄准角测量系统(PAMS)。本报告描述系统的工作原理和软件技术。本报告的结论是:在跟踪点确定的范围内,PAMS的跟踪精度在规定的     

国外地面防空火控雷达的现状和发展趋向

现代防空作战任务对地（舰）空导弹、高炮、弹炮结台武器系统中火控雷达的基本要求;现役地面防空火控雷达的现状;未来10年内,地面防空火控雷达的发展趋向。     

如何提高小高炮雷达对近程快速目标的跟踪性能

本文就火控系统中的小高炮雷达,如何提高近距离目标的跟踪精度和跟踪速度这两项重要战术指标问题,指出克服速度动态滞后采用指挥仪速度正反馈控制;而解决加速度动态滞后,提出了加速度误差修正控制方案,并推导出数学模型和列举具体实施方案以及测试结果。     

高炮系统反应时间分析

本文对高炮系统反应时间进行了分析,并对目标跟踪的反应时间做了定量描述;提出缩短系统反应时间的一些措施和途径。     

某高炮武器系统自动校射系统设计

我国现役高炮火控系统的校射大多采用开环控制,没有自动校射功能,作战效能较低.针对某型高炮设计了一种自动校射系统,该系统采用火控解算参数与数字图像处理技术相结合的方法,火控计算机计算出虚拟弹目偏差,图像处理技术获取置信度较高的弹目偏差,对高炮射击诸元进行实时校正,克服传统校射的不足,从而实现对高炮武器系统的全过程高精度自...     

高炮人-机跟踪系统建模及动态特性分析

本文以某高炮人-机系统为对象,以人的最优控制模型为基础,建立该人-机跟踪系统部分的数学模型,利用计算机求解——即模型预测方法,研究操作者(炮手)在跟踪沿不同航路飞行的空中目标时系统的跟踪误差和动态性能;与此同时研制一套模拟原高炮人-机系统的仿真试验装置,以获取的试验数据做为检验上述模型预测结果和进行全系统性能分析的依据。     

多层局部回归神经网络在激光陀螺捷联惯导系统惯性敏感器误差补偿中的应用

惯导系统误差补偿技术对提高武器装备的性能具有重要的意义 ,而误差补偿的关键在于误差模型的辨识。探讨将多层局部回归神经网络引入到惯性敏感器误差建模中 ,详细介绍了网络结构和对应的自适应动态梯度算法。仿真算例说明 ,多层局部回归神经网络在惯性敏感器输出误差建模时具有一定的优点 :网络收敛速度快、较好的跟踪性能、稳定性好。     

Finite-time tracking control and vibration suppression based on the concept of virtual control force for flexible two-link space robot

The dynamic modeling, finite-time trajectory tracking control and vibration suppression of a flexible two-link space robot are studied. Firstly, the dynamic model of the system is established by combining Lagrange method with assumed mode method. In order to ensure that the base attitude and the joints of space robot can reach the desired positions within a limited time, a non-singular fast terminal sliding mode (NFTSM) controller is designed, which realizes the finite-time convergence of the trajectory tracking errors. Subsequently, for the sake of suppressing the vibrations of flexible links, a hybrid tra-jectory based on the concept of the virtual control force is developed, which can reflect the flexible modes and the trajectory tracking errors simultaneously. By modifying the original control scheme, a NFTSM hybrid controller is proposed. The hybrid control scheme can not only realized attitude stabili-zation and trajectory tracking of joints in finite time, but also provide a new method of vibration sup-pression. The simulation results verify the effectiveness of the designed hybrid control strategy.     

Integrated guidance and control of guided projectile with multiple constraints based on fuzzy adaptive and dynamic surface

Based on fuzzy adaptive and dynamic surface (FADS), an integrated guidance and control (IGC) approach was proposed for large caliber naval gun guided projectile, which was robust to target maneuver, canard dynamic characteristics, and multiple constraints, such as impact angle, limited measurement of line of sight (LOS) angle rate and nonlinear saturation of canard deflection. Initially, a strict feedback cascade model of IGC in longitudinal plane was established, and extended state observer (ESO) was designed to estimate LOS angle rate and uncertain disturbances with unknown boundary inside and outside of system, including aerodynamic parameters perturbation, target maneuver and model errors. Secondly, aiming at zeroing LOS angle tracking error and LOS angle rate in finite time, a nonsingular terminal sliding mode (NTSM) was designed with adaptive exponential reaching law. Furthermore, combining with dynamic surface, which prevented the complex differential of virtual control laws, the fuzzy adaptive systems were designed to approximate observation errors of uncertain disturbances and to reduce chatter of control law. Finally, the adaptive Nussbaum gain function was introduced to compensate nonlinear saturation of canard deflection. The LOS angle tracking error and LOS angle rate were convergent in finite time and whole system states were uniform ultimately bounded, rigorously proven by Lyapunov stability theory. Hardware-in-the-loop simulation (HILS) and digital simulation experiments both showed FADS provided guided projectile with good guidance performance while striking targets with different maneuvering forms.     

基于阵列式探测器的舰载高能激光武器动态精度试验方法研究

对高机动目标的跟踪、瞄准精度是舰载高能激光武器系统的重要性能指标之一，也是未来装备状态鉴定和列装定型工作的主要考核项目。以舰载高能激光武器为研究对象，系统分析了其动态精度试验的技术特点，在此基础上，针对其跟踪瞄准精度要求高的实际问题，提出了基于阵列式探测器的试验和数据处理方法，能够有效完成对舰载高能激光武器动态精度的试验与评估。     

Adaptive sliding mode control of modular self-reconfigurable spacecraft with time-delay estimation

The reconstruction control of modular self-reconfigurable spacecraft (MSRS) is addressed using an adaptive sliding mode control (ASMC) scheme based on time-delay estimation (TDE) technology. In contrast to the ground, the base of the MSRS is floating when assembled in orbit, resulting in a strong dynamic coupling effect. A TED-based ASMC technique with exponential reaching law is designed to achieve high-precision coordinated control between the spacecraft base and the robotic arm. TDE technology is used by the controller to compensate for coupling terms and uncertainties, while ASMC can augment and improve TDE’s robustness. To suppress TDE errors and eliminate chattering, a new adaptive law is created to modify gain parameters online, ensuring quick dynamic response and high tracking accuracy. The Lyapunov approach shows that the tracking errors are uniformly ultimately bounded (UUB). Finally, the on-orbit assembly process of MSRS is simulated to validate the efficacy of the proposed control scheme. The simulation results show that the proposed control method can accurately complete the target module’s on-orbit assembly, with minimal perturbations to the spacecraft’s attitude. Meanwhile, it has a high level of robustness and can effectively eliminate chattering.     

Barrier Lyapunov functions-based dynamic surface control with tracking error constraints for ammunition manipulator electro-hydraulic system

This paper focuses on the dynamic tracking control of ammunition manipulator system. A standard state space model for the ammunition manipulator electro-hydraulic system (AMEHS) with inherent non-linearities and uncertainties considered was established. To simultaneously suppress the violation of tracking error constraints and the complexity of differential explosion, a barrier Lyapunov functions-based dynamic surface control (BLF-DSC) method was proposed for the position tracking control of the ammunition manipulator. Theoretical analysis prove the stability of the closed-loop overall system and the tracking error converges to a prescribed neighborhood asymptotically. The effectiveness and dynamic tracking performance of the proposed control strategy is validated via simulation and experi-mental results.     

基于小波去噪半参数回归模型的卫星轨道测量数据预处理方法

由于卫星轨道测量数据中含有非线性误差,使用传统的最小二乘多项式拟合方法对其进行预处理必然会降低定轨精度.在半参数回归模型的基础上,应用小波阈值去噪算法估计并消除观测数据中存在的非线性误差,提出了基于小波去噪半参数回归模型的卫星轨道测量数据预处理方法,以提高数据预处理的精度.对某卫星USB跟踪数据应用该方法进行了仿真,仿真结果表明:该方法可以分离出观测数据中的白噪声和非线性误差,从而可以在观测数据中消除非线性误差的影响,提高数据预处理的精度.     

RCS特性辅助的CMIMO雷达功率资源分配方法

针对集中式多输入多输出(collocated multiple-input multiple-output, CMIMO)雷达在实际探测过程中,未有效结合目标雷达散射截面(radar cross section, RCS)高动态变化特性导致雷达跟踪精度不高甚至失跟的问题,提出一种基于目标RCS高动态特性的CMIMO雷达功率资源自适应分配方法。考虑到目标RCS特征的角度敏感性,利用目标运动状态的可预测性动态获取实际观测角度,从而完成跟踪帧的极化方式优选;在此基础上构建包含功率与RCS的多目标跟踪误差后验克拉美罗下界,将其作为目标函数进行优化,利用内点惩罚法求解该凸优化问题即可实现RCS高动态情况下的功率优化分配。实验结果表明:该方法可结合目标不同方向RCS动态分集特性实现功率的有效分配,相比于传统RCS模型分配方案,有效解决了分配方案与实际跟踪场景之间的失配问题,从而提升了CMIMO雷达的多目标跟踪性能。     

机动目标模型研究与发展综述

对机动目标模型的研究与发展进行了回顾,指出了各个模型的局限性,重点对Singer模型和“当前”统计模型的优缺点进行了分析,并得到有意义的结论;最后指出了未来机动目标模型研究的方向和趋势。