捷联式惯性导航

该论文主要研究如何用数字信号处理芯片（DSP：TMS320VC33PGA120）和复杂可编程逻辑器件（CPLD：EPM7128STC-100）作为数字硬件平台，实现捷联式惯性导航系统（SINS）高速实时数据处理的硬件、软件设计。

The paper mainly focuses on the software and hardware design that the data real-time processes of the SINS , using the DSP and the CPLD as the digital hardware platform .

捷联式惯性导航系统算法研究

Research on the Algorithm for SINS

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 .

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 .

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 .

捷联式惯性导航系统单兵导弹捷联惯导系统IMU测量误差模型

Measurement Error Model of IMU in Strapdown Inertial Guidance System of Manpads Missile

本文以实际科研项目为背景，对以捷联式惯性导航（SINS）为核心的自主式水下航行器导航技术进行了研究，并实现了导航系统的仿真设计。

Based on actual AUV project , this thesis mainly studies the navigation system , which is based on strapdown inertial navigation ( SINS ) .

为实现满足中低精度要求的低成本导航系统，选用MEMS惯性传感器研制了捷联式惯性导航系统（SINS）；

In order to implement low cost navigation system which meets the needs of medium and low accuracy , developed MEMS strapdown inertial navigation system ( SINS );

作为舰船、飞机、航天器等载体上的重要设备，捷联式惯性导航系统（SINS）无论在军用还是民用领域，都发挥着重要作用。

In both military and civil areas Strapdown Inertial Navigation System ( SINS ) plays such an important role as necessary equipment on vessels , planes , aircraft , and so on .

然而，微机电系统（MEMS）的快速发展为这一问题带来了解决方案，基于MEMS的惯性器件以其自身体积小、成本低、功耗低等特点在室内捷联式惯性导航应用方面有了广泛研究。

However , the rapid development of MEMS brings a solution to this problem . For its small size , low cost and low power consumption , inertial device based on MEMS has been studied extensively in the area of indoor inertial navigation applications .

阐述了应用于捷联式惯性导航系统（SINS）中的通用高性能多路脉冲信号采集器的具体工程设计，提出了完成其主体功能的可编程逻辑器件（PLD）详细设计方法。

The paper introduces the designing techniques of general hign - performance multiplex pulse acquisition in strapdown inertial navigation system ( SINS ), and mentions the designing methods with PLD ( Programmable Logic Device ) to perform the main function .

捷联式惯性导航系统性能的综合评价新方法

Comprehensive Performance Evaluation of the Navigation System Based on Triangular Fuzzy Numbers

船用捷联式惯性导航系统仿真器的设计和研究

Design and Study of the Simulator of Marine Strapdown Inertial Navigation System

易于实现的捷联式惯性导航系统仿真

The Easy Approach Using Simulation on Strap-down Inertial Navigation System

运用对偶四元数代数研究了捷联式惯性导航的误差特性。

Error characteristics of the strapdown inertial navigation are investigated using dual quaternion .

捷联式惯性导航系统中的陀螺仪工作于锁定状态，其锁定是由再平衡回路完成的。

The gyroscope in strapdown inertial navigation system is caged by its rebalance loop .

在分析捷联式惯性导航系统作用原理的基础上，对其误差传播特性进行了分析。

It also analyses the strap-down inertial navigation system role principle and its error propagation .

捷联式惯性导航设备辅助导线纵联保护装置

Strapdown inertial navigation equipment pilot-wire protectio

捷联式惯性导航系统惯性元件的设置与可靠性

On the Disposition of the Inertial Units and the Reliability of the Strapdown Inertial Navigation System

随着惯性仪器、仪表技术的发展，光纤陀螺仪结构简单，性能稳定性显著提高，以及其成本低，体积小，重量轻等优点，使其尤其适合捷联式惯性导航系统的应用。

With the development inertial instruments , FOG has advanced and fits for the application of strapdown navigation .

讨论了捷联式惯性导航系统的误差，对位置计算中的涡卷误差进行了推证。

It is discussed that the system error and dynamic error , especially the dynamic error in position algorithm .

因此，为了提高捷联式惯性导航系统的精度，必须建模分析研究温度对陀螺零偏的影响。

To improve the accuracy of SINS , we must analyze the influence of temperature on the null-shift of laser gyro .

本文给出了捷联式惯性导航系统一种简单实用的场地标定方法。

A simple and utility field fast calibration method for the gyroflex strapdown inertial system has been presented in this paper .

传统采用的捷联式惯性导航系统对微型移动机器人运动状态的估计是利用了较高精度的陀螺来确定其位姿、加速度计来确定其位置。

Traditional strap-down inertial navigation system uses high-accuracy gyroscope and accelerometer to get the azimuth and the position of the mini-mobile robot .

捷联式惯性导航系统以其可靠性高、体积小、重量轻，成本低的特点正逐步取代平台式惯导系统。

Strap-down INS gradually take place of Platform INS because of its higher reliability , smaller size , lighter weight and lower cost .

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。

The attitude solution for carrier is one of the key technologies for precision navigation of Strapdown Inertial Navigation System ( SINS ) .

本文从惯性导航基本方程出发，推导了激光陀螺捷联式惯性导航系统的系统级标定的一种误差标定模型。

In this paper , based on the inertial navigation equation , a novel model for the laser gyro strapdown inertial navigation system is provided .

捷联式惯性导航系统以固连在载体上的陀螺组件与加速度组件为敏感元件，利用载体上的导航计算机解算出当前的位置、姿态信息。

The computer on the strap-down inertial navigation system calculates the location and attitude of the vector , which uses gyro and accelerator as sensor components .

捷联式惯性导航系统误差处理的研究在近年来取得很大进展，相继出现了一些新思想、新算法、新技术。

In recent years , more advances have been made in the research on error process for Strapdown Inertial Navigation ( SINS ), accompanied with new ideas , algorithms and technology .

运用对偶四元数代数重新诠释捷联式惯性导航的基本原理，得到了三个对偶四元数运动学方程，其形式均与姿态四元数微分方程一致。

Through reinterpreting the rationale of the strapdown inertial navigation in terms of dual quaternion algebra , we obtain three dual quaternion kinematic equations that take the same forms as the conventional attitude quaternion rate equation .