基于传感器网络的分布式生化气体源参数测定算法

针对生化气体源参数测定问题,提出了一种基于传感网络的分布式贝叶斯迭代估计算法,该算法在给定气体物理分布扩散模型条件下,通过传感器节点获取气体浓度,并基于分布式扩展卡尔曼滤波（EKF）和无迹卡尔曼滤波（UKF）实现气体源的坐标定位和释放率估计.通过仿真实验对两种分布式算法进行性能分析,结果表明,UKF算法在参数估计成功率和参数估计误差两个方面均要好于EKF算法,分别可以提高约50%和70%,其收敛速度快,使用节点少,更有助于节省网络能量消耗,并延长其生存周期.     

基于分布式算法FIR滤波器的FPGA设计

FIR滤波器是一种被广泛应用的基本的数字信号处理部件。针对采用常用方法设计实现FIR滤波器存在的问题,提出基于分布式算法设计并在FPGA上高效实现严格线性相位FIR滤波器的方案,通过编程仿真得到满意的结果。该方法实现FIR滤波器器件体积小、性能可靠、价格低廉、设计周期短,可作为高速数字滤波设计的较好方案。     

小型微带带通滤波器的设计

利用多条微带线间的耦合增加滤波器内部的耦合度,提出一种小型窄带带通滤波器的设计;从微带线的等效分布电感电容出发,结合模拟和试验结果以及滤波器结构参数对滤波特性的影响,提出该滤波器的等效LC电路模型以及计算中心工作频率的经验公式.数值模拟和试验结果验证了该设计思想.     

IIR数字滤波器设计方法

用双线性变换法设计IIR数字滤波器并解决了下列问题 :双线性变换的原理 ;数字滤波器的频率与相似图形的模拟滤波器的频率的转化在及模拟滤波器的数字化方法。     

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.     

基于学习进化的机器人同时定位与地图创建

利用学习与进化结合的思想,改善基于粒子滤波的SLAM算法。在对学习与进化的关系深入分析的基础上,针对基于粒子滤波的SLAM算法,提出将滤波过程分成学习和进化两个阶段,分别给出相应算法解决粒子有效性与多样性的问题,缓解二者之间的矛盾,改善了SLAM算法的效果,增强了算法的鲁棒性,也验证了学习与进化的关系。最后,通过多次Monte-Carlo仿真实验结果表明了该算法的有效性。     

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.     

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.     

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.