一种适用于时序InSAR的同质像元加权干涉相位滤波方法

为了有效地利用多时相InSAR的时间维度信息, 并保证滤波窗口内像元的同质性, 提出一种同质像元加权干涉相位滤波方法。首先采用拟合优度检验, 对多时相SAR 图像的同质像元进行识别, 然后在同质像元之间进行加权干涉相位滤波, 以保证中心像元在滤波过程中不受周边非同质像元干扰。基于真实干涉SAR图像的实验结果表明, 与经典Goldstein滤波及Lee滤波相比, 该滤波方法在目视效果、相位残差点数量及相位导数标准差3个指标上具有优势, 实现滤波器的设计初衷。     

一种低资源数字抽取滤波器设计

设计并实现一个应用于音频Sigma-Delta模数转换器的低资源数字抽取滤波器。该滤波器采用多级多采样率结构, 整体带内纹波小于0.06 dB, 带宽为21.6 kHz, 最低工作频率为10 MHz。通过滤波器硬件架构的设计, 有效地缩小了抽取滤波器的电路面积和功耗。芯片测试结果表明, 对 64 倍过采样率、4 阶Sigma-Delta调制的 1 bit 脉冲密度调制信号输出码流进行处理, 得到音频信号的信噪比达到87.2 dB, 在SMIC 0.13 μm 工艺下, 数字部分的面积约为0.146 mm²。与同类型抽取滤波器相比, 面积减小58%, 功耗减少60%以上。     

相干测风激光雷达带通采样方法的仿真研究

根据相干测风雷达回波信号载频高、带宽窄的特点,尤其星载相干测风雷达回波信号数千兆赫兹,采用传统采样方式对采集卡的采样率要求很高.鉴于采集卡的采样率和分辨力互相制约,提出将带通采样引入到相干测风雷达系统.本文以1.5 μm全光纤相干测风激光雷达的实测数据作为仿真输入,经Simulink滤波、带通采样,结果表明,在对探测距离影响不大的情况下,与低通采样方式相比径向风速反演结果最大相差0.5 μm/s;数据处理的时间复杂度降低,其下降值是带通采样频率与低通采样频率的比值;但信噪比会恶化,其下降值介于1~3 dB.      

单相交流输入永磁同步电机功率变换电路研究

针对单相正弦交流电源供电的永磁同步电机控制系统的功率变换电路进行研究。对滤波电容、整流管BR的电流以及控制系统主电路的参数进行了分析和计算,并推导出关键参数的计算公式,通过实验验证了电路参数计算方法的可行性。该研究对功率变换电路的设计具有一定的参考价值。     

有色观测噪声下的多变量设置调整策略

针对存在初始设置偏差的离散的多变量生产制造过程，研究了观测噪声服从Auto-Rgressive （AR）模型的情况下，考虑调整花费成本为二次型函数时的设置调整问题，在建立过程状态空间方程的基础上，利用卡尔曼滤波方法在线估计过程的状态变量，根据随机二次型最优控制理论，得到了使过程质量损失最小的最优调整策略. 通过算例解释了最优调整策略的实现方法，并进行了仿真验证，结果表明，得到的调整策略与观测噪声为白噪声时的质量调整策略相比，能更好地减少过程总体质量损失.     

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.     

基于卡尔曼滤波的多滑模面电动舵机控制

针对导弹用力矩电机的位置反馈控制,提出一种采用多滑模面自适应变结构控制法,采用卡尔曼滤波器估计状态,消除测量噪声,降低输出抖动,对多滑模面控制率的稳定与收敛性进行适当证明,通过仿真验证算法的有效性。     

GPSNISNAV integrated relative navigation and attitude determination system for ultra-close spacecraft formation flying

For the improvement of accuracy and better fault-tolerant performance, a global position system (GPS)/vision navigation (VISNAV) integrated relative navigation and attitude determination approach is presented for ultra-close spacecraft formation flying. Onboard GPS and VISNAV system are adopted and a federal Kalman filter architecture is used for the total navigation system design. Simulation results indicate that the integrated system can provide a total improvement of relative navigation and attitude estimation performance in accuracy and fault-tolerance.     

一种应用于二进制传感器网络的目标跟踪算法

针对采用集中式粒子滤波方法解决二进制传感器网络目标跟踪问题存在的实时性较差和网络能量消耗大的缺点，提出了一种基于动态分簇的分布式粒子滤波算法。以随着目标运动而动态变化的簇为信息处理结构，簇头节点收集簇成员的单跳测量信息，实时对目标状态进行估计，非簇内节点进入休眠状态以节省能量。仿真表明，合理设置簇转换距离和激活半径，算法的跟踪精度与集中式粒子滤波方法相当；在不影响跟踪效果的情况下，可适当减小簇转换距离和激活半径，从而节省网络能量。