基于强跟踪UKF 的自适应SLAM 算法

针对无迹卡尔曼滤波（UKF）缺乏在线自适应调整能力,导致系统状态估计精度较低的问题,提出了 一种将强跟踪滤波器（STF）与UKF 相结合的SLAM 算法．该算法对于UKF 中每个采样点采用STF 进行更新,获 得优化滤波增益,抑制噪声对系统状态估计的影响,使系统状态估计迅速收敛到真实值附近．仿真实验对比了当前 几种SLAM 算法在不同噪声环境下的性能,实验表明,基于强跟踪UKF 的自适应SLAM 算法具有更好的鲁棒性和 自适应性．     

改进粒子滤波与预测滤波相结合的单星敏姿态估计

针对卫星姿态估计的非线性、非高斯特性,提出一种粒子滤波和预测滤波相结合的估计方法,在无角速率测量时,首先利用预测方法在线估计系统模型误差和姿态角速度,再通过改进的规则化粒子滤波器估计姿态四元数.粒子初始化和重要性函数等的设计加快了算法的收敛速度,预测方法的引入有效降低了粒子维数.在某通用小卫星平台上进行仿真,并与扩展卡尔曼滤波(EKF)比较,所得结果表明,算法在不同初始姿态估计时具有较好的稳定性和收敛精度.算法还为粒子滤波和无陀螺定姿的研究提供了参考.     

非线性预测滤波在星敏感器姿态确定中的应用

为研究无陀螺卫星控制优化问题的新方法,针对环境干扰力矩和估计误差等不确定因素导致滤波器稳定性和估计精度降低,提出了使用星敏感器测量值在线估计模型参数和卫星姿态的非线性预测滤波方法.根据预测滤波理论推导了关于模型误差的损失函数,利用线性化的测量方程求得使损失函数最小化的模型误差值,代人状态方程求数值积分,得到卫星的姿态估计参数.仿真结果证明,不仅简化了计算,且适应性更强.而应用四元数描述卫星姿态,避免了欧拉角法的奇异性问题.仿真结果还表明,方法收敛速度较EKF更快,状态估计精度与EKF相当,并对非线性模型误差具有良好的跟踪性能.     

一种改进的基于概率假设密度滤波的多目标跟踪方法

针对概率假设密度（PHD）滤波使用聚类方法提取目标状态时,会出现结果不准确,且PHD滤波无法给出状态到航迹关联的问题,提出一种在目标状态中加入标签的方法来实现状态到航迹的关联．该方法对权值较大的标签,通过两次确认来剔除杂波干扰,得到比传统PHD滤波更精确的状态估计．在提取目标状态时,只对相同标签的粒子进行处理,避免使用聚类方法．通过与传统PHD算法的仿真对比表明,改进算法具有较好的跟踪性能．     

基于高斯粒子群优化的RBPF滤波算法

针对动态系统目标跟踪问题,RBPF算法通过将高维状态空间分解成易于处理的线性子部分与非线性子部分,并采取不同策略进行滤波估计。为了提高RBPF的计算效率,提出将粒子群优化思想融入到RBPF滤波估计中,凭借粒子群算法卓越的全局搜索能力,对于状态空间中非线性部分,通过粒子群算法驱使所有采样粒子向高似然区域(最优适应值区域)移动;对于线性状态部分,依然利用卡尔曼滤波进行处理。通过多组实验仿真结果对比,PSO-RBPF利用较少采样粒子、耗费较少时间即能获得极佳的估计精度。     

多传感器系统的延长周期全信息融合滤波

提出了基于系统状态预测信息、子系统状态预测信息及量测信息的多传感器系统全信息融合滤波方法.针对多传感器系统中子系统状态估计信息与系统状态预测信息之间存在相关性的问题,采用延长系统融合器融合周期的方法来弱化它们之间的相关性,再进行直接融合来获得系统状态估计.基于"GPS姿态敏感器+陀螺"模式组合的卫星姿态确定系统的仿真结果表明了延长周期全信息融合滤波方法的有效性.     

基于自适应表面模型的概率视频跟踪算法

提出一种鲁棒自适应表面模型,该模型中每个像素值的变化过程由一混合高斯分布描述．为了适应目标表面的变化,这些高斯参数在跟踪期间通过在线的EM算法自适应更新;在估计目标状态时。采用了粒子滤波算法。设计了基于自适应表面模型的观测模型;在处理遮挡时,采用了一种鲁棒估计技术．多组试验结果表明,该算法对光照变化、姿态变化、部分或完全遮挡下的跟踪具有较强的鲁棒性．     

一种强跟踪有限差分滤波二元估计算法

针对非线性工业过程测量的滞后性和模型不确定性给系统状态估计和模型参数估计造成的困难,在扩展Kalman滤波器（EKF）的基础上,引入有限差分滤波器（FDEKF）和次优渐消因子,提出了一种强跟踪有限差分滤波状态和参数二元估计算法。该二元估计算法将滤波器分解为参数滤波和状态滤波两个过程,分别估计模型参数和系统状态。最后,将该算法应用于一化学反应过程的仿真,结果表明,这种强跟踪有限差分滤波的二元估计算法在原模型或参数存在偏差的情况下,仍能较准确地估计系统状态和模型参数,并具有较强的数值鲁棒性。     

噪声统计特性不确定下的卫星姿态估计

姿态确定算法是卫星姿态确定系统的重要组成部分。在姿态确定系统中广泛采用卡尔曼滤波作为姿态确定算法，但是卡尔曼滤波依赖于噪声统计特性的先验知识，采用不精确的噪声统计特性设计卡尔曼滤波器可能会导致较大的估计误差，甚至造成滤波发散。本文针对噪声统计特性的不确定性分别采用了自适应卡尔曼滤波器和预测滤波器估计卫星姿态，通过数学仿真验证在噪声统计特性不确定的情况下。这两种滤波器仍然可以较精确地估计卫星姿态。     

迭代测量更新CDKF的粒子滤波方法

为了提高中心差分卡尔曼粒子滤波（CDKFPF）算法跟踪时的估计精度,提出了一种基于迭代测量更新CDKF的粒子滤波（ICDKFPF）新算法。该算法利用迭代中心差分卡尔曼滤波的最大后验概率估计产生粒子滤波的重要性密度函数,并用Levenberg-Marquardt方法对状态协方差进行修正,使粒子的观测信息得到充分有效的利用,更加符合真实状态的后验概率分布。仿真结果表明,所提出算法的估计性能要明显优于标准的粒子滤波（PF）和中心差分卡尔曼粒子滤波（CDKFPF）。     

Marginalized particle filter for spacecraft attitude estimation from vector measurements

An algorithm based on the marginalized particle filters (MPF) is given in details in this paper to solve the spacecraft attitude estimation problem: attitude and gyro bias estimation using the biased gyro and vector observations. In this algorithm, by marginalizing out the state appearing linearly in the spacecraft model, the Kalman filter is associated with each particle in order to reduce the size of the state space and computational burden. The distribution of attitude vector is approximated by a set of particles and estimated using particle filter, while the estimation of gyro bias is obtained for each one of the attitude particles by applying the Kalman filter. The efficiency of this modified MPF estimator is verified through numerical simulation of a fully actuated rigid body. For comparison, unscented Kalman filter (UKF) is also used to gauge the performance of MPF. The results presented in this paper clearly demonstrate that the MPF is superior to UKF in coping with the nonlinear model.     

Marginalized particle filter for spacecraft attitude estimation from vector measurements

An algorithm based on the marginalized particle filters （MPF） is given in details in this paper to solve the spacecraft attitude estimation problem： attitude and gyro bias estimation using the biased gyro and vector observations. In this algorithm, by marginalizing out the state appearing linearly in the spacecraft model, the Kalman filter is associated with each particle in order to reduce the size of the state space and computational burden. The distribution of attitude vector is approximated by a set of particles and estimated using particle filter, while the estimation of gyro bias is obtained for each one of the attitude particles by applying the Kalman filter. The efficiency of this modified MPF estimator is verified through numerical simulation of a fully actuated rigid body. For comparison, unscented Kalman filter （UKF） is also used to gauge the performance of MPE The results presented in this paper clearly derfionstrate that the MPF is superior to UKF in coping with the nonlinear model.     

面向皮纳卫星姿态确定的MEMS陀螺磁强计组合滤波系统

针对难以配置高精度部件的皮纳卫星姿态测量系统,当卫星处于阴影区或任何太阳敏感器不可用的状态下,MEMS陀螺与磁强计的组合便成为卫星在轨姿态测量精度的重要保障.本文基于MEMS陀螺与磁强计的低功耗、全轨、全天时、最小姿态敏感组合,提出一种适用于皮纳卫星在轨运行的滤波系统方案.该方案通过滑窗ARMA建模降低陀螺随机噪声的影响,并由姿态滤波器估计所得的零偏在线去除陀螺常值分量,以保证其建模的长期有效性.本文以浙江大学皮星二号卫星搭载的敏感部件以及姿态测量算法为研究基础,结合在轨实测数据,仿真对比表明,该系统方案有效降低了陀螺随机噪声,抑制比达50％以上;陀螺零偏估计精度提高310％,可达到0.001°/s;姿态确定精度提升190％,可达1.2127°.该系统方案是对皮纳卫星姿态确定最小系统精度提升及实用方案设计的有益探索.     

UKF based in‐flight calibration of magnetometers and rate gyros for pico satellite attitude determination

In this paper an unscented Kalman filter based procedure for the bias estimation of both the magnetometers and the gyros carried onboard a pico satellite, is proposed. At the initial phase, biases of three orthogonally located magnetometers are estimated as well as the attitude and attitude rates of the satellite. During the initial period after the orbit injection, gyro measurements are accepted as bias free since the precise gyros are working accurately and the accumulated gyro biases are negligible. At the second phase estimated constant magnetometer bias components are taken into account and the algorithm is run for the estimation of the gyro biases that are cumulatively increased by time. As a result, six different bias terms for two different sensors are obtained in two stages, where attitude and attitude rates are estimated regularly. For both estimation phases of the procedure an unscented Kalman filter is used as the estimation algorithm. Copyright © 2011 John Wiley and Sons Asia Pte Ltd and Chinese Automatic Control Society     

自主姿态测量算法研究

航姿系统一般不实时计算速度和位置信息,无法补偿地球自转和表观运动引起的分量误差,同时陀螺漂移较大,载体长时间持续机动时,出现姿态精度不高,甚至发散的问题。提出了一种基于卡尔曼滤波的姿态融合算法,将等效陀螺漂移列入系统状态,利用卡尔曼滤波的新息对运动状态进行判别,在一定条件下,用加速度计的输出作为量测量进行卡尔曼滤波的量测更新过程。实验结果表明,所提出的姿态融合算法考虑了陀螺漂移,能提高载体长时间机动时的姿态精度。     

Box particle filtering for nonlinear state estimation using interval analysis

In recent years particle filters have been applied to a variety of state estimation problems. A particle filter is a sequential Monte Carlo Bayesian estimator of the posterior density of the state using weighted particles. The efficiency and accuracy of the filter depend mostly on the number of particles used in the estimation and on the propagation function used to re-allocate weights to these particles at each iteration. If the imprecision, i.e. bias and noise, in the available information is high, the number of particles needs to be very large in order to obtain good performances. This may give rise to complexity problems for a real-time implementation. This kind of imprecision can easily be represented by interval data if the maximum error is known. Handling interval data is a new approach successfully applied to different real applications. In this paper, we propose an extension of the particle filter algorithm able to handle interval data and using interval analysis and constraint satisfaction techniques. In standard particle filtering, particles are punctual states associated with weights whose likelihoods are defined by a statistical model of the observation error. In the box particle filter, particles are boxes associated with weights whose likelihood is defined by a bounded model of the observation error. Experiments using actual data for global localization of a vehicle show the usefulness and the efficiency of the proposed approach.     

应用于多旋翼MAVs的姿态测量系统

应用一个三轴加速度计、三个单轴角速率陀螺和一个三轴磁强计等微机械惯性传感器,设计廉价轻量姿态测量系统,研究了姿态角推算算法。在以往的姿态测量系统中,陀螺偏差和动加速度的影响限制其应用。将角速度陀螺的误差作为状态量导入到系统,动加速度作为噪音项导入到观测方程中,然后利用扩展卡尔曼滤波器来构成姿态估计算法来降低误差。实际飞行中对比商用高精度传感器和多次室外飞行测试表明,设计的系统能够应于旋翼MAVs。     

Fault tolerant attitude estimation for an LEO satellite using a multi-hypothesis filter

The aim of this paper is to improve state estimation and FDI performance. We proposed an algorithm using a model based multi-hypothesis filter (MHF). With this method, we can detect and identify the fault on a satellite actuator. Also, we can improve the attitude estimation performance of a satellite attitude control system. In this method, there are several models for a possible failure situation and the model probabilities are decided from the residuals of each filter. The master filter finds the most suitable state estimation result from the weighting sum of each filter based on probabilities. And a probability crossing detection algorithm and thresholding algorithm based on probabilities are introduced for fault detection and identification of satellite actuators. The simulation results demonstrate the advantages of the MHF-based method proposed.     

非线性系统的多扩展目标跟踪算法

目前扩展目标跟踪算法大都假设其系统为线性高斯系统，针对非线性系统的多扩展目标跟踪问题，提出了采用粒子滤波技术对目标状态和关联假设进行联合估计的多扩展目标跟踪算法。首先，提出了将多扩展目标状态和关联假设进行联合估计的思想，解决了在估计目标状态和数据关联时相互牵制的问题；其次，根据扩展目标演化模型、量测模型建立多扩展目标状态和关联假设的联合建议分布函数，并利用粒子滤波技术实现联合估计的Bayes框架；最后，为解决直接采用粒子滤波实现时存在的维数灾难问题，将目标联合状态粒子的产生和演化分解为各个目标状态粒子的产生和演化，对每个目标的粒子集根据与其相关的权重单独进行重抽样，这样在抑制目标状态估计较差部分的同时使每个目标都保留了对其状态估计较好的粒子。仿真实验结果表明，与扩展目标概率假设密度滤波器的高斯混合实现方式和序贯蒙特卡洛实现方式相比，所提算法的状态估计精度较高，形状估计的Jaccard距离分别降低了30%、20%左右，更适合于非线性系统的多扩展目标跟踪。