被动雷达导引头多脉冲辐射源的角度分辨与跟踪

讨论了被动雷达导引头主波束内存在多脉冲辐射源时对多辐射源进行角度分辨并跟踪某一辐射源的方法。首先利用聚类分析法实现多辐射源角度分辨 ,然后利用主波束角度压缩方法实现单一辐射源跟踪。计算机仿真结果表明 :在中等密度脉冲辐射源环境下 ,采用聚类分析和主波束角度压缩相结合的方法可较好地实现导引头主波束内多脉冲辐射源的角度分辨与单一辐射源跟踪     

双点源干扰诱偏被动雷达导引头性能分析

以经典的双点源干扰模型为基础,简要说明了在双点源干扰下导引头的静态跟踪误差。在此基础上,研究了动态下的攻防对抗,建立了数学模型并仿真,得出了攻击误差。仿真分析了双干扰源功率变化时导弹的攻击轨迹和误差,以及功率不相等时干扰源间距和天线波束宽度对诱骗效果的影响。仿真结果表明:只要参数合适,非相干双点源干扰可以很好的诱骗导引头,达到保护目标的目的。     

捷联寻的制导弹药的新型卡尔曼滤波器设计

针对捷联制导系统的自身特点,设计出用于估计导弹和目标在弹体坐标系中相对运动状态的卡尔曼滤波器,使滤波与制导在同一个坐标系即弹体坐标系内进行,避免了信息在弹体坐标系和惯性坐标系之间的多次转换,从而减少了信息损失.仿真结果表明,该方法能够满足捷联制导系统的要求.     

高动态和角速率输入下捷联算法比较研究

在常规弹箭上应用固态微惯系统具有重要意义.该文研究各种航姿算法对常规弹箭高动态运动特征的适应性.以高动态规则进动作为运动输入,仿真四元数航姿算法和旋转矢量多子样算法的漂移.误差分析和数值仿真结果表明:高动态环境下,引入了角速率项的旋转矢量修正二子样算法能较好地适应由新型固态陀螺构建的捷联系统.     

激光制导炸弹导引头的光电建模

激光制导炸弹导引头能否正确提取激光光斑信号是激光制导炸弹正常工作的关键，它与激光指示器对目标的照射能力、激光在大气中的传输以及导引头相对激光光斑的位置等条件密切相关。根据激光制导炸弹导引头的结构和工作原理建立了激光导引头探测激光光斑的数学模型，并通过仿真得到了激光光斑在炸弹典型投放条件下的变化规律。     

捷联惯导系统仿真器的设计

提出了一种通用捷联惯导系统仿真器的设计方案、根据捷联惯导系统的特点，利用面向对象技术进行模块分解，设计出了可以模拟多种环境、扩展性很强的仿真器，为相关导航系统算法的验证提供数据源、     

激光制导炸弹数字仿真研究

以激光制导航空炸弹为例，建立了该型炸弹的导引头模型、控制系统模型和六自由度空间运动模型。在MATLAB环境中，通过使用SIMULINK工具箱，对该型炸弹进行了数字仿真研究。仿真结果为后续的半实物仿真提供了基础。     

基于改进型BP神经网络的导引头测高性能评估

武器装备性能评估贯穿于装备发展的全寿命过程,对于装备定型与实战化运用具有重要意义。针对传统反向传播(back propagation, BP)神经网络模型易陷入局部最优、武器装备评估数据少等问题,提出了基于数据包络分析和Bootstrap法的改进型BP神经网络模型。利用数据包络分析处理原始指标得到3项优化参数,结合Bootstrap法对其进行扩充,再通过BP神经网络建立评估模型。实验表明,改进模型得到的合成孔径雷达(systemic aperture radar, SAR)导引头测高性能评估结果,其决定系数和误差系数均有明显改善。该模型不仅规避了模糊综合评判法主观性强、精确度不高等问题,同时有效解决了传统BP神经网络模型易陷入局部最优和武器装备评估数据少的两个问题。     

New rapid transfer alignment method for SINS of airborne weapon systems

Transfer alignment is an effective alignment method for the strapdown inertial navigation system （SINS） of airborne weapon systems. The traditional transfer alignment methods for large misalignment angles alignment use nonlinear transfer align- ment models and incorporate nonlinear filtering. A rapid transfer alignment method with linear models and linear filtering for ar- bitrary misalignment angles is presented. Through the attitude quaternion decomposition, the purpose of transfer alignment is converted to estimate a constant quaternion. Employing special manipulations on measurement equation, velocity and attitude linear measurement equations are derived. Then the linear trans- fer alignment model for arbitrary misalignment angles is built. An adaptive Kalman filter is developed to handle modeling errors of the measurement noise statistics. Simulation results show feasibili- ty and effectiveness of the proposed method, which provides an alternative rapid transfer alignment method for airborne weapons.     

Self-alignment of full skewed RSINS：observability analysis and full-observable Kalman filter

Traditional orthogonal strapdown inertial navigation sys-tem （SINS） cannot achieve satisfactory self-alignment accuracy in the stationary base： taking more than 5 minutes and al the iner-tial sensors biases cannot get ful observability except the up-axis accelerometer. However, the ful skewed redundant SINS （RSINS） can not only enhance the reliability of the system, but also improve the accuracy of the system, such as the initial alignment. Firstly, the observability of the system state includes attitude errors and al the inertial sensors biases are analyzed with the global perspective method： any three gyroscopes and three accelerometers can be assembled into an independent subordinate SINS （sub-SINS）;the system state can be uniquely confirmed by the coupling connec-tions of al the sub-SINSs;the attitude errors and random constant biases of al the inertial sensors are observable. However, the ran-dom noises of the inertial sensors are not taken into account in the above analyzing process. Secondly, the ful-observable Kalman filter which can be applied to the actual RSINS containing random noises is established; the system state includes the position, ve-locity, attitude errors of al the sub-SINSs and the random constant biases of the redundant inertial sensors. At last, the initial self-alignment process of a typical four-redundancy ful skewed RSINS is simulated： the horizontal attitudes （pitch, rol ） errors and yaw error can be exactly evaluated within 80 s and 100 s respectively, while the random constant biases of gyroscopes and accelero-meters can be precisely evaluated within 120 s. For the ful skewed RSINS, the self-alignment accuracy is greatly improved, mean-while the self-alignment time is widely shortened.