scholarly journals Parameter Identification Method for SINS Initial Alignment under Inertial Frame

2016 ◽  
Vol 2016 ◽  
pp. 1-9 ◽  
Author(s):  
Haijian Xue ◽  
Xiaosong Guo ◽  
Zhaofa Zhou
Keyword(s):  
Parameter Identification ◽  
Inertial Frame ◽  
Alignment Algorithm ◽  
Alignment Method ◽  
Initial Alignment ◽  
Dynamic Disturbance ◽  
Identification Method ◽  
Reference Information ◽  
External Reference ◽  
Alignment Model

The performance of a strapdown inertial navigation system (SINS) largely depends on the accuracy and rapidness of the initial alignment. The conventional alignment method with parameter identification has been already applied widely, but it needs to calculate the gyroscope drifts through two-position method; then the time of initial alignment is greatly prolonged. For this issue, a novel self-alignment algorithm by parameter identification method under inertial frame for SINS is proposed in this paper. Firstly, this coarse alignment method using the gravity in the inertial frame as a reference is discussed to overcome the limit of dynamic disturbance on a rocking base and fulfill the requirement for the fine alignment. Secondly, the fine alignment method by parameter identification under inertial frame is formulated. The theoretical analysis results show that the fine alignment model is fully self-aligned with no external reference information and the gyrodrifts can be estimated in real time. The simulation results demonstrate that the proposed method can achieve rapid and highly accurate initial alignment for SINS.

scholarly journals Initial Self-Alignment for Marine Rotary SINS Using Novel Adaptive Kalman Filter

2015 ◽  
Vol 2015 ◽  
pp. 1-12 ◽  
Author(s):  
Fujun Pei ◽  
Li Zhu ◽  
Jian Zhao
Keyword(s):  
Kalman Filter ◽  
Inertial Frame ◽  
Error Model ◽  
Alignment Method ◽  
Initial Alignment ◽  
Adaptive Kalman Filter ◽  
Dynamic Disturbance ◽  
System Error ◽  
Angular Velocities ◽  
Initial Attitude

The accurate initial attitude is essential to affect the navigation result of Rotary Strapdown Inertial Navigation System (SINS), which is usually calculated by initial alignment. But marine mooring Rotary SINS has to withstand dynamic disturbance, such as the interference angular velocities and accelerations caused by surge and sway. In order to overcome the limit of dynamic disturbance under the marine mooring condition, an alignment method using novel adaptive Kalman filter for marine mooring Rotary SINS is developed in this paper. This alignment method using the gravity in the inertial frame as a reference is discussed to deal with the lineal and angular disturbances. Secondly, the system error model for fine alignment in the inertial frame as a reference is established. Thirdly, PWCS and SVD are used to analyze the observability of the system error model for fine alignment. Finally, a novel adaptive Kalman filter with measurement residual to estimate measurement noise variance is designed. The simulation results demonstrate that the proposed method can achieve better accuracy and stability for marine Rotary SINS.

scholarly journals In-Flight Alignment UsingH∞Filter for Strapdown INS on Aircraft

2014 ◽  
Vol 2014 ◽  
pp. 1-8 ◽  
Author(s):  
Fu-Jun Pei ◽  
Xuan Liu ◽  
Li Zhu
Keyword(s):  
Inertial Navigation System ◽  
Inertial Frame ◽  
Alignment Error ◽  
System State ◽  
Alignment Method ◽  
Initial Alignment ◽  
Dynamic Disturbance ◽  
Aircraft Flight ◽  
Value Decomposition ◽  
Constant System

In-flight alignment is an effective way to improve the accuracy and speed of initial alignment for strapdown inertial navigation system (INS). During the aircraft flight, strapdown INS alignment was disturbed by lineal and angular movements of the aircraft. To deal with the disturbances in dynamic initial alignment, a novel alignment method for SINS is investigated in this paper. In this method, an initial alignment error model of SINS in the inertial frame is established. The observability of the system is discussed by piece-wise constant system (PWCS) theory and observable degree is computed by the singular value decomposition (SVD) theory. It is demonstrated that the system is completely observable, and all the system state parameters can be estimated by optimal filter. Then aH∞filter was designed to resolve the uncertainty of measurement noise. The simulation results demonstrate that the proposed algorithm can reach a better accuracy under the dynamic disturbance condition.

An Improved Initial Alignment Method of Strap-Down Inertial Navigation System on a Swaying Base

2013 ◽  
Vol 415 ◽  
pp. 143-148
Author(s):  
Li Hua Zhu ◽  
Xiang Hong Cheng
Keyword(s):  
Navigation System ◽  
Inertial Navigation System ◽  
Alignment Algorithm ◽  
Alignment Method ◽  
Initial Alignment ◽  
Vehicle Simulation ◽  
Robust Property ◽  
Simulation Results ◽  
Lever Arm Effect ◽  
The Impact

The design of an improved alignment method of SINS on a swaying base is presented in this paper. FIR filter is taken to decrease the impact caused by the lever arm effect. And the system also encompasses the online estimation of gyroscopes’ drift with Kalman filter in order to do the compensation, and the inertial freezing alignment algorithm which helps to resolve the attitude matrix with respect to its fast and robust property to provide the mathematical platform for the vehicle. Simulation results show that the proposed method is efficient for the initial alignment of the swaying base navigation system.

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

Measurement ◽  
2014 ◽  
Vol 55 ◽  
pp. 593-604 ◽  
Author(s):  
Xixiang Liu ◽  
Xiaosu Xu ◽  
Yu Zhao ◽  
Lihui Wang ◽  
Yiting Liu
Keyword(s):  
Apparent Motion ◽  
Inertial Frame ◽  
Alignment Method ◽  
Initial Alignment

Fast Fine Initial Self-alignment of INS in Erecting Process on Stationary Base

2017 ◽  
Vol 71 (3) ◽  
pp. 697-710 ◽  
Author(s):  
Jianli Li ◽  
Yiqi Li ◽  
Baiqi Liuxs
Keyword(s):  
Navigation System ◽  
Inertial Navigation System ◽  
Inertial Navigation ◽  
Euler Angle ◽  
Alignment Method ◽  
State Variables ◽  
Initial Alignment ◽  
Angle Error ◽  
Alignment Model ◽  
System Observability

Fine initial alignment is vital to the Inertial Navigation System (INS) before the launching of a missile. The existing initial alignment methods are mainly performed on a stationary base after the missile has been erected to the vertical state. However, these methods consume extra alignment time and some state variables have poor degrees of observability, thus losing the rapidity of alignment. In order to solve the problem, a fast fine initial self-alignment method of a missile-borne INS is proposed, which is performed during the erecting process on a stationary base. The convected Euler angle error is modelled to optimise the erecting manoeuvre which can prevent large Euler angle errors and improve the system observability. The fine initial alignment model is established to estimate and correct the initial misalignment. Several experiments verify that the proposed method is effective for improving the rapidity of the fine initial alignment for a missile-borne INS.

Research on Independent Coarse Alignment of Aircraft Carriers SINS

2012 ◽  
Vol 591-593 ◽  
pp. 1827-1830
Author(s):  
Tao Yuan ◽  
Jing Shuo Xu ◽  
Ya Zhou Di
Keyword(s):  
Signal To Noise Ratio ◽  
Alignment Algorithm ◽  
Alignment Method ◽  
Initial Alignment ◽  
Aircraft Carrier ◽  
Velocity Signal ◽  
Earth Gravity ◽  
The Earth ◽  
Moving Base ◽  
Gravity Acceleration

Carrier-based Aircraft closely watched as the aircraft carrier weapons, storms and other factors affect the generated carrier swing to sway.This will enable the gyro measurement to the Earth's rotation angular velocity signal to noise ratio dropped significantly, giving the aircraft carrier's initialaligned to bring difficulties. To solve this problem, the Earth gravity acceleration in the inertial space the SINS independent coarse alignment, and gives the process of acceleration due to gravity points vector of analytic coarse alignment and fine alignment algorithm. Theoretical analysis and simulation results show that the moving base SINS alignment method can effectively solve the initial alignment of the aircraft carrier in the state of the ship mooring.

Map Matching-Aided In-Motion SINS Initial Alignment

2012 ◽  
Vol 605-607 ◽  
pp. 1395-1401
Author(s):  
Gao Wei Zhang ◽  
Jia Bin Chen ◽  
Chun Lei Song ◽  
Ting Ting Wang
Keyword(s):  
Inertial Frame ◽  
Dead Reckoning ◽  
Alignment Algorithm ◽  
Map Matching ◽  
Positioning Error ◽  
Test Results ◽  
Initial Alignment ◽  
Integrated Map ◽  
Matching Algorithm ◽  
Land Vehicles

The paper introduces a novel in-motion SINS initial alignment algorithm using the inertial frame as computing reference. First, dead reckoning method is utilized with the help of the external odometer speed information aiming to eliminate the angular and linear moving disturbances. Second, in order to suppressing the divergence of the positioning error, a new integrated Map Matching algorithm is introduced which is able to reduce the effect of misalignment angle from coarse alignment for positioning error. Road test results show that this algorithm has greatly reduced the coarse alignment of directional accuracy and saved the requirements of speed and route for land vehicles. Not only is the mobility of land vehicle enhanced but also the accuracy of initial alignment of inertial navigation system is improved, which is meaningful in real application.

scholarly journals Research on initial alignment method of vehicle-mounted SINS based on reverse navigation

2021 ◽  
Vol 1846 (1) ◽  
pp. 012075
Author(s):  
Chen Yang ◽  
Yuanwen Cai ◽  
Chaojun Xin ◽  
Meiling Shi
Keyword(s):  
Alignment Method ◽  
Initial Alignment

scholarly journals Parameter identification method of hydraulic automatic gauge control system based on chaotic wolf pack optimization algorithm

AIP Advances ◽  
2021 ◽  
Vol 11 (5) ◽  
pp. 055302
Author(s):  
Yong Zhu ◽  
Guangpeng Li ◽  
Shengnan Tang ◽  
Wanlu Jiang ◽  
Zhijian Zheng
Keyword(s):  
Control System ◽  
Parameter Identification ◽  
Optimization Algorithm ◽  
Identification Method ◽  
Automatic Gauge Control
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