捷联惯导系统

圆锥误差补偿算法在三轴激光捷联惯导系统中的应用

Application of Conning Compensation Algorithm in Three-axis Laser SINS

主要研究导弹发射升空以后，通过星敏感器测星实现对捷联惯导系统中陀螺仪误差参数的实时修正技术。

The real-time correction of gyroscope error parameter in SINS by star sensor was researched .

用C语言实现捷联惯导系统的输入输出功能

Realizing Input / Output Functions of SINS in C Language

Matlab在捷联惯导系统试验航路设计中的应用

Application of Matlab in the Sea Route Design of SINS Experiment

某捷联惯导系统的BIT设计与实现

Design and Realization of BIT for SINS Electrocircuits

基于H∞的低精度捷联惯导系统初始对准方法

An Approach for Initial Alignment of Low-accuracy SINS Based on H_ ∞ Filter

推导了载体非质心处的比力方程，并给出了无陀螺捷联惯导系统的解算流程，为编制DSP应用程序奠定了基础。

The specific force equation at the noncentraled of the body is deduced .

讨论了基于DSP的捷联惯导系统的硬件设计，包括基本功能的实现、原理框图及外围电路的设计。

The hardware of the DSP-based strapdown inertial guidance system is introduced in details .

基于FPGA的激光陀螺捷联惯导系统信号的检测与处理

Signal Detecting and Processing of Strapdown Inertial Navigation System with Ring Laser Gyroscope Based on FPGA

基于MEMS的低成本捷联惯导系统实现

The Low Cost Inertial Navigation System Based on MEMS

通过车载试验验证了这种捷联惯导系统FPGA硬件实现的可行性。

Through car test , it is shown that the FPGA hardware implementation of SINS is feasible .

然后针对整个捷联惯导系统，使用Matlab语言编制了从轨迹生成、到惯导解算处理的仿真模块，验证了惯导算法的导航功能。

Then for the whole navigation system , the modules of trace-generation and SINS calculation are programmed using Matlab language .

提出了一种基于多天线GPS载波相位测量的捷联惯导系统静基座初始对准方法。

A new initial alignment method for SINS stationary base is proposed which is aided by multi-antennas GPS carrier phase measurement .

基于OpenGL的捷联惯导系统可视化仿真实现

The Realizing of Visualized Simulation Based on OpenGL in Strapdown Inertial Navigation System

以车比雪夫大数定律为基础，研究基于捷联惯导系统（SINS）的全球卫星定位系统（GPS）完善性监测方法。

A new approach of GPS integrity based on SINS is studied by means of the Chebyshevs law of great numbers .

数据采集是捷联惯导系统设计的关键，本文数据采集由信号调理、A/D转换和FPGA等几部分组成。

In this paper , the data acquisition is composed of signal conditioning , A / D conversion , FPGA and so on .

用GPS测得的导航信息校正无陀螺捷联惯导系统的导航参数误差，提高导航精度，并且可以用于长时间导航。

During motion the navigation parameter errors are adjusted by the data obtained from GPS , which meet the accuracy and time requirements for navigation systems .

基于DSP和CPLD技术的激光陀螺捷联惯导系统小型化导航CPU板的研制

The Development of Miniaturization Navigation CPU Board Based on the Technology of DSP and CPLD Applied in Laser Gyro Strapdown Inertial Navigation Systems

针对捷联惯导系统对于精度和实时性等要求，介绍了基于DSP的捷联惯导数据采集系统的构成及技术实现。

The construction and techno-realization of strapdown inertial navigation data collection system are presented in accordance with the requests on precision and real time in this system .

本文以一个低成本压电陀螺捷联惯导系统及其与GPS的组合为对象，做了以下几方面的研究工作。

This paper regards a low cost piezoelectricity gyro SINS and integration of it and GPS as the target , make the research work of the following aspects .

针对捷联惯导系统的并行捷联解算算法和并行卡尔曼滤波初始对准算法的FPGA实现，分别从系统的角度进行了详细分析。

From the perspective of system , the FPGA implementation of parallel strapdown algorithm and parallel Kalman filter initial alignment algorithm is analyzed in detail , respectively .

本文提出了基于Unscented转换的Unsented卡尔曼滤波进行捷联惯导系统对准的方法。

An approach of unscented kalman filter based on unscented transformation is presented .

提出适用于低成本捷联惯导系统的初始对准方法，即采用非线性对准模型和采样卡尔曼滤波（UnscentedKalmanFilter）进行状态估计。

An initial alignment method for low-cost SINS is proposed , which uses nonlinear error model and the unscented Kalman filter ( UKF ) .

基于IMU旋转的捷联惯导系统自补偿方法

Auto-compensation method of SINS based on IMU rotation

本文对捷联惯导系统（SINS）及其与全球定位系统（GPS）的组合导航系统进行了研究。

In this paper , the strap-down inertial navigation system ( SINS ) and the integrated navigation of SINS and global positioning system ( GPS ) are studied .

针对捷联惯导系统（SINS）的算法设计，介绍了SINS的姿态、速度和位置基本微分方程组；

The attitude , velocity and position differential equations of Strapdown Inertial Navigation System ( SINS ) for the design of SINS algorithm were introduced .

捷联惯导系统（SINS）静基座初始对准时，由于方位误差角的观测度较低，使对准的时间比较长。

When the stationary SINS initial alignment is in process , it usually takes rather long time because of low observability of the azimuth misalignment angle .

同时，当故障发生时，由于融合了系统信息，它能使重构的系统以更高的精度工作.采用这种滤波器设计了捷联惯导系统、GPS、多普勒雷达三传感器信息容错系统。

Based on three sensors ' ( strapdown system , GPS receiver , Doppler radar ) information fusion , a fault-tolerant navigation system is designed with this information fusion filter and two-ellipsoid overlap test .

研究了一种新的捷联惯导系统（SINS）动基座误差模型及载体动基座对准时的最优机动方式问题。

A new error model of strapdown inertial navigation system ( SINS ) and the optimal maneuver of vehicles in-flight alignment had been studied on moving bases .

针对初始对准过程中对准精度与快速性相矛盾的问题，提出并设计了把扩张状态观测器（ESO）与卡尔曼滤波滤波估计器相结合，用于捷联惯导系统初始对准的方法。

A fast initial alignment method for SINS is proposed which combines Extended States Observers ( ESO ) with Kalman filters .