惯性导航系统

但其位置误差是随时间积累的，因此单独惯性导航系统无法满足长期高精度导航定位要求。

However , its position error accumulates over time , so the single INS cannot meet the requirements of long-term and high-precision navigation and positioning .

在此基础上，分析了未来高精度惯性导航系统5m/hr的定位精度对重力场分辨率和精度的要求。

At these base , the requirements to the resolution and the accuracy of gravity in the next precision INS with 5m / hr horizontal position error are analysed .

利用差分GPS提高惯性导航系统飞行测试基准的精度

Utilize Differential GPS for Improving INS Flight Testing Reference System Performance

GPS姿态测量系统对惯性导航系统误差修正能力分析

Analysis for Capability of INS Error-Correction Based on GPS Attitude Determination System

GPS定姿系统/捷联惯性导航系统组合技术研究

Research on SINS / GPS Attitude Determination System

DSP在无陀螺惯性导航系统中的应用

Application of Digital Signal Processor ( DSP ) in Gyroscope Free Inertial Navigation System

SINS（Strap-downInertialNavigationSystem）是捷联式惯性导航系统的简称，它是惯性导航系统的一种。

SINS is a strap-down inertial navigation system .

基于MEMS技术的微型惯性导航系统的发展现状

Evolution of MEMS Based Micro Inertial Navigation Systems

惯性导航系统（InertialNavigationSystem，INS）不需要外部信息，具有自主性强的特点。

Inertial Navigation System ( Inertial Navigation System , INS ) does not need external information and has highly autonomous character .

简单阐述了差分GPS、惯性导航系统INS及GPS／INS组合系统的有关基本原理。

Describes the basic principles of differential GPS , inertial navigation system and integrated GPS / INS system .

对基于SAR图像匹配定位的地形辅助惯性导航系统的原理进行了充分阐述；

The theory of terrain-aided navigation system has been presented , which is based on the matching of SAR images .

∑-Δ型adc对惯性导航系统中加速度信号影响的分析

Analysis for the Influence of Σ - Δ ADC on Accelerometer Signals in Inertial Navigation System

它是集GPS技术、北斗卫星导航技术、高动态载体姿态测定的惯性导航系统、激光技术以及影像采集系统与一体的技术。

It represents a collection of GPS technology , BD Guided technology , dynamic pose measurement inertial navigation system , laser technology and image Acquisition System .

应用卡尔曼滤波方法，对采用GPS姿态测量信息对惯性导航系统的误差修正能力进行分析和仿真。

By adopting the Kalman filtering method , the capability of correcting the error of inertial navigation system using GPS attitude information is analyzed and simulated .

本论文采用Visualc++和OpenGL编程语言，严格按照对象的数学方程或动力学方程进行仿真，用三维的形式展示了惯性导航系统中的概念。

This dissertation uses the 3D visualization models to express the INS with Visual C + + and OpenGL by mathematics or dynamics equations .

捷联惯性导航系统（SINS）和全球定位系统（GPS）构成的组合导航系统应用广泛。

Integrated navigation system constituted by strapdown inertial navigation system ( SINS ) and Global Positioning System ( GPS ) was widely used .

论文首先介绍了捷联式惯性导航系统、GPS导航系统和多普勒计程仪的基本原理及各自特点，并建立了捷联惯性导航系统的非线性误差模型。

Firstly , the paper introduced the basic theory and characteristics of the Strapdown Inertial Navigation System ( SINS ), the GPS , and the DVL system .

本文通过对GPS和INS（惯性导航系统）算法和特点的研究，建立了GPS/INS组合导航系统的模型；

In the paper through researching feature and algorithm of GPS and INS , Establish model of GPS / INS integrated navigation system .

高速、高精度的圆锥偿补算法是提高捷联惯性导航系统（SINS）性能的重要环节。

High speed and high accuracy coning algorithm plays a key role in strapdown inertial navigation system ( SINS ) .

在此基础上将卡尔曼滤波和H∞滤波应用于捷联式惯性导航系统的初始对准，并对此进行了仿真分析。

Based on it , Kalman filter and Hx filter are applied to the initial alignment of Strapdown INS and , in addition , an analysis of simulation is made .

该系统通过综合技术将惯性导航系统与差分GPS有效组合，不仅定位精度高、工作可靠，而且输出信息实时、连续；

The system , by effectively integrating INS / DGPS , is not only with high positioning accuracy and working reliability , but also outputs real time and continuous information .

捷联惯性导航系统（StrapdownInertialNavigationSystem，SINS）是二十世纪初发展起来的一种不受外界干扰的自主式导航系统。

Strapdown Inertial navigation system ( SINS ) is a kind of autonomous navigation system that developed in the early twentieth century , and it free from outside interference .

之后论文较为详细的介绍了惯性导航系统的基本算法和基于粒子滤波器的SLAM算法。

And then the Inertial Navigation System and the SLAM algorithm based on particle filter are introduced detailedly .

捷联惯性导航系统一般会如激光陀螺、光纤陀螺和MEMS等体积小的惯性器件。

In general , strapdown inertial navigation system use small size inertial devices such as laser gyro , fiber optic gyro and inertial MEMS devices .

为了解决航海型平台式惯性导航系统（INS）非自主式初始对准问题，建立了不同观测量条件下统一的INS初始对准方程。

A novel approach was proposed to solve the non-autonomous initial alignment problem of marine gimbal inertial navigation system ( INS ) .

本课题是以教研室自主研发项目光纤陀螺捷联惯性导航系统（Fiber-OpticGyroscopeStrapdownInertialNavigationSystem）的研究为背景的。

The paper is based on the research and development of the project named " SINS ( Strapdown Inertial Navigation System ) based on FOG ( Fiber-Optic Gyroscope )" .

惯性导航系统（INS）以其自主的工作能力广泛应用于军事武备的导航、制导与控制系统和国民经济的诸多领域。

Inertial navigation system ( INS ) is used widely in many military and civil scopes because of its ability of independent operation .

其次将GPS姿态确定系统应用于捷联惯性导航系统的动基座初始对准研究，基于传递对准的概念，推导了系统误差方程；

Second , the GPS attitude determination system is applied to the initial alignment of SINS on moving base . The system error equations are deduced based on the concept of transfer alignment .

组合导航技术一直是导航领域重点研究方向，而如何将高精度全球定位系统（GPS）和可靠的捷联惯性导航系统（SINS）结合起来更是具有广阔的研究空间。

Integrated navigation system is always the emphases in the study of navigation field and there is very broad space in the research of combining high-accuracy GPS and high-reliability SINS .

研究了船用INS与GPS姿态测量系统组合的组合导航系统，并对GPS姿态测量系统信息对惯性导航系统的误差修正能力进行了仿真。

After the establishment and research of the integrated navigation system of INS and GPS attitude determination system , the capability of INS error-correction based on GPS attitude determination is simulated .