捷联惯导系统姿态解算模块的实现

提出了一种实现捷联惯性导航系统姿态解算模块的方法。基于DSP的硬件平台和四元数的数学平台,设计了捷联惯性导航系统的姿态解算模块。介绍了捷联惯性导航系统的工作原理和姿态解算的基本算法,并给出了四元数法的四阶龙格一库塔数值解法。设计了姿态解算模块的硬件电路和软件实现程序。实验测试结果表明,在增量角〈5°的情况下,用四阶龙格一库塔法进行姿态解算,误差〈0．0053％;应用TMS320C6713B进行硬件电路设计,每次解算时间〈36μs,能够满足捷联惯性导航系统对精度和速度的要求。     

基于四元数法的捷联式惯性导航系统姿态解算研究

为实现捷联式惯性导航系统的精确导航,载体的姿态解算算法是核心技术之一。首先分析了欧拉法、方向余弦法、四元数法求解姿态矩阵的优缺点,根据四元数法与方向余弦法两种解算方法分别进行计算,两种方法的计算结果之差与理论真值比较以得到解算的相对误差,从而验证了四元数法的正确性和有效性,最后提出提高采样频率和采用高阶计算算法能进一步减小姿态解算误差。数字化仿真与转台试验结果表明,根据本文所述算法进行载体姿态解算的误差很小,具有良好的实时性,为捷联式惯性导航技术的工程实践提供了依据。     

基于四元数法的捷联式惯性导航系统的姿态解算

载体的姿态解算算法是实现捷联式惯性导航系统精确导航的核心技术之一。分析了欧拉法、方向余弦法、四元数法求解姿态矩阵的优缺点,采用四元数法与方向余弦法两种解算方法分别计算载体姿态,两种方法的计算结果之差与理论真值比较以得到解算的相对误差,从而验证了四元数法的正确性和有效性。最后,指出提高采样频率和采用高阶计算算法能进一步减小姿态解算误差。数字化仿真与转台试验结果表明,本文提出的载体姿态解算法的理论数值相对误差为10^-10％,测试实验相对误差为10^3％,计算时间为36μs,具有良好的实时性。     

基于MPU6050的四轴硬件姿态解算研究

针对四轴飞行器姿态信息的实时准确获取问题,对四轴飞行器的姿态解算方面进行了研究。在分析姿态表示的四元数法和欧拉角法基础上,以成熟的Mahony互补滤波算法为例比较了软件姿态解算和基于MPU6050数字运动处理器(DMP)的硬件姿态解算的实现流程,并对两种解算方法的解算时间和对姿态变化的跟踪性能进行了实验测试。研究结果表明:硬件姿态解算能实时准确地获取小型四轴飞行器的各项姿态信息,可以满足小型四轴飞行器的姿态控制要求。     

几种数值算法在弹道微分方程组解算中的仿真与比较

本文简述了数值分析的应用范围,介绍了微分方程几种不同的数值解法,及其在弹道解算中的应用。在简化弹丸弹道动力学微分方程的基础上,通过 Mablab 软件编写欧拉法、梯形法、经典四阶龙格库塔法程序,计算动力学微分方程组近似解及各种方法的局部截断误差和计算时间。通过对结果的分析比较,明确了几种经典解法在弹道解算中的优劣,为弹道解算方法的选择提供了依据。     

几种数值算法在弹道微分方程组解算中的仿真与比较（英文）

本文简述了数值分析的应用范围,介绍了微分方程几种不同的数值解法,及其在弹道解算中的应用。在简化弹丸弹道动力学微分方程的基础上,通过Mablab软件编写欧拉法、梯形法、经典四阶龙格库塔法程序,计算动力学微分方程组近似解及各种方法的局部截断误差和计算时间。通过对结果的分析比较,明确了几种经典解法在弹道解算中的优劣,为弹道解算方法的选择提供了依据。     

机械传动扭振计算方法

根据矩阵迭代法和四阶龙格——库塔法，应用TC语言编制了求解扭振系统的全部特征值、待证向量、系统固有频率、主振型及在任意载荷下动态扭矩的计算程序．同时在586计算机上调试通过．文中算例的计算结果与实测值取得比较一致的结果．     

基于四元数二阶互补滤波的四旋翼姿态解算

姿态解算是四旋翼飞行器的关键技术,其精度直接影响飞行器控制的可靠性和稳定性。针对当前常用一阶互补滤波算法中阻带衰减速率慢和陀螺仪常值漂移产生的稳态误差问题,通过增加积分环节,设计了一种基于四元数的二阶互补滤波算法,能更好地利用加速度计和磁力计的稳态信息有效补偿陀螺仪常值漂移,从而减少姿态解算的累积误差。仿真结果表明,该算法具有更好的稳定性,提高了系统的姿态解算精度。通过飞行器真实飞行数据对算法进行了实验验证,结果显示姿态的俯仰角、横滚角精度1°,偏航角精度2°,能很好地满足飞行器控制系统对姿态解算的精度要求。     

捷联惯导系统误差模型与仿真分析

为研究捷联惯导系统短时间导航精度,建立了导航误差数学模型,分析了惯性器件误差对系统导航精度的影响。应用捷联惯性导航原理,针对系统短时间导航的特点,简化载体在导航坐标系的导航方程;由惯性器件安装误差与陀螺仪等效零漂经过方向余弦矩阵变换建立载体姿态误差方程;结合导航方程、姿态误差方程与惯性器件误差推导出载体速度误差与位置误差数学模型。在此基础上,建立了误差状态空间方程与误差模型框图。在Matlab/Simulink环境下建立了误差数学模型计算模块,用捷联惯导算法与误差模型共同解算地面150秒导航试验数据,结果表明：导航系X轴的相对系统误差小于20%,Y轴、Z轴的相对系统误差小于5%,验证了误差数学模型的正确性。此外,分析了加速度计精度的变化对短时间工作的捷联惯导系统导航误差产生基本的影响。     

离子阱质谱中离子轨迹算法研究

高精度数值仿真算法是研究离子阱中离子的运动特征、仿真设计与优化离子阱质谱仪器的关键。本研究探讨了2种基于四阶、五阶龙格-库塔算法的数值方法,求解离子在离子阱内的运动方程--Mathieu方程。通过Matlab编程进行离子轨迹仿真实验,计算精度、初值、时间步长等因素对计算结果的影响。结果表明,五阶龙格-库塔算法可以满足离子阱的仿真要求,能实现高精度离子轨迹计算。     

Strapdown gyrocompass algorithm for AUV attitude determination using a digital filter

The strapdown gyrocompass can provide attitude by measuring the Earth’s gravity vector. In practical applications, there usually exists unwanted disturbance accelerometers that will distort the accelerometer measurements, hence a filtering out procedure is essential. Current attitude determination method based on pendulum cutting off technology has the limitation for vehicle moving mode. This paper proposes a new strapdown gyrocompass algorithm via processing the accelerometer measurement with Butterworth low-pass filter (LPF) to remove the high frequency dynamic disturbance components. When the gravity variation in inertial frame is regulated, LPF can be applied to properly get the gravity even in the presence of acceleration disturbances, and subsequently can be applied to calculate the strapdown gyrocompass attitude. The proposed algorithm does not require declination information and inertial element biases estimation. The field test has been conducted and the results verified the effectiveness and reliability of the proposed AUV attitude determination method and have also shown that the gravity is proportional to the latitude and altitude of AUV.     

一种激光断面仪运动补偿用IMU/GPS/OD系统

针对车载激光路面断面仪性能受检测车垂直振动及姿态变化影响的问题,设计并实现了一种车载激光断面仪运动补偿用IMU/GPS/OD组合测量系统,采用低成本IMU结合捷联解算算法计算检测车的三维位置、速度和姿态,通过GPS和里程仪结合最优滤波技术抑制低成本IMU在捷联解算过程中形成的累积误差,并提出了一种基于IMU/GPS/OD组合测量系统的检测车垂直振动位移的计算方法。最后进行了室内实验验证,实验结果表明,该IMU/GPS/OD组合测量系统应用于车载激光断面仪是可行的。     

状态χ2检验法在惯性航姿系统内阻尼卡尔曼滤波器中的应用

本文探讨了如何利用惯性测量组合本身的信息来提高捷联航姿系统的姿态精度。根据平台式阻尼网络的思想，设计了捷联式内阻尼卡尔曼滤波器，将惯导系统捷联解算获得的姿态与加速度计估计的姿态进行组合，在系统非加速度状态下，提高了姿态输出的精度。为了实时监测系统的运动状态从而判断内阻尼姿态的有效性，本文成功将状态χ2检验法应用在内阻尼卡尔曼滤波器中，设计了基于2个状态传播器的故障监测器，并通过对故障检测向量元素的检验代替对整个向量的检验，提高了故障监测的灵敏度和可靠性。最后，实际系统的动静态实验验证了本文所提出的方法的有效性。     

An initial alignment method for strapdown gyrocompass based on gravitational apparent motion in inertial frame

Inspired by the alignment mechanism of Octans, an initial alignment method for strapdown gyrocompass is designed based on gravitational apparent motion in inertial frame. In this method, the gyro outputs are used to trace the body frame and the measurement from accelerometers are projected to the inertial frame to form the track of gravitational apparent motion. According to the calculations on the vectors involved in this track, the attitude matrix between the inertial frame and navigation frame can be obtained and further alignment can be finished. In order to identify the true gravitational apparent motion from the accelerometer measurement containing random noise as well as to avoid the collinear of vectors in vector operation, a reconstruction algorithm concerning parameter identification and reconstruction of apparent motion is devised and simulated. Simulation and turntable test show that the proposed alignment method can realize self-alignment in a swinging condition. The alignment accuracy is able to reach the theoretical one determined by sensor errors and no external information is needed.     

A novel algorithm for marine strapdown gyrocompass based on digital filter

With the rapid development of strapdown gyrocompass, few corresponding strapdown algorithms occur in publications, so that we have to use the conventional one designed for platform gyrocompass. Enlightened by IXSEA ideals, we proposed a novel algorithm which is suitable for marine strapdown gyrocompass. In our proposed algorithm, gyro outputs are used to track the body frame rotation, and the observation of the pure gravity slow drift in the inertial gives the navigation frame rotation. We also separate the pure gravity from interferential accelerations with a FIR low-pass digital filter. The analysis and numerical results show the better performance of the proposed algorithm than the conventional one.     

二进制鲁棒不变尺度特征匹配电子稳像

针对捷联图像制导系统中视频序列受弹体姿态变化和抖动而出现的不稳定现象,提出了一种基于二进制鲁棒不变尺度特征关键点(BRISK)的高精度快速鲁棒电子稳像算法。首先,用BRISK算法提取图像BRISK特征描述符;为了保证匹配精度和速度,采用引导互匹配策略实现BRISK特征点跟踪匹配;然后,利用改进的随机抽样一致方法(RANSAC)剔除误匹配点对;最后,利用最小二乘算法(LSA)估计全局运动参数进而实现稳像。对标准图片的匹配测试和实拍视频稳像的结果表明:结合BRISK算法的电子稳像技术,运行时间小于30ms,定位精度达到0.1pixel,对光照变化、噪声以及复杂环境遮挡具有较强的鲁棒性,能快速有效地补偿捷联制导图像的复杂随机抖动并提高视频质量。     

融合 WiFi 与可穿戴惯导模块的室内定位方法

为解决基于智能手机的人员室内定位追踪易受手机姿态影响的问题,提出一种融合WiFi与可穿戴惯导模块的室内定位方法。通过固定在胸部的惯性测量单元实现行人航迹推算PDR)定位,消除手机姿态对PDR定位的影响,采用加权贝叶斯算法实现WiFi指纹定位,为PDR提供初始定位,同时基于无迹卡尔曼滤波融合WiFi定位结果与PDR定位结果,以减少PDR的累积定位误差。最后,在真实室内环境中进行大量实验,实验结果证明本文提出的加权贝叶斯WiFi定位算法相比于传统贝叶斯算法定位误差降低了51.9%,提出的融合WiFi与可穿戴惯导模块的定位方法具有更好的精度和稳定性,相比于纯PDR定位算法平均定位误差降低了65.2%,相比于完全利用手机实现的融合算法,在3种不同手机姿态下平均定位误差分别下降了12.3%、39.3%和48.4%。     

Initial orientation of inertial navigation system realized through nonlinear modeling and filtering

Alignment is the process whereby the orientation of the axes of an inertial navigation system is determined with respect to the reference system. In this paper, the initial alignment error equations of the strapdown inertial navigation system (SINS) with large initial azimuth error have been derived with inclusion of nonlinear characteristics. Simulations have been carried out to validate and corroborate the stationary alignment case employing a strapdown inertial measurement unit (SIMU). A performance comparison between the extended Kalman filter (EKF), the unscented Kalman filter (UKF) and the second-order divided difference filter (DDF2) demonstrate that the accuracy of attitude error estimation using the DDF2 is better than that of using the EKF or the UKF.     

Random misalignment and lever arm vector online estimation in shipborne aircraft transfer alignment

Shipborne aircrafts normally do not have regular position on the carrier. This would lead to large misalignment between the master strapdown inertial navigation system (M-SINS) and slave strapdown inertial navigation system (S-SINS) as well as random lever arm vector. It is critical for the accuracy of the transfer alignment. The large attitude error will make the linear alignment algorithm invalid. And the lever arm vector caused by the location difference will lead to the lever arm effect which is sensed by the accelerometers in the S-SINS. Therefore it is necessary for the shipborne aircraft to estimate the lever arm vector and misalignment before the transfer alignment takes place. In this paper, a new misalignment and lever arm vector online estimation method based on gyroscope, accelerometer measurement and filtering is presented. Sensor measurements of M-SINS and S-SINS will be recorded for a few seconds. Misalignment and the lever arm vector will be calculated from these measurements directly. The values will be filtered according to the chosen threshold of the error gain. Then a second stage estimation based on least square estimation will be applied to acquire a better result. Simulation results demonstrate the effectiveness of the estimation algorithm in the situation when both large misalignment and random lever arm vector exist.