AN INTEGRATED AIRCRAFT NAVIGATION SYSTEM WITH OPTICAL HORIZON SENSOR

Aviation ◽  
2012 ◽  
Vol 16 (4) ◽  
pp. 109-114 ◽  
Author(s):  
Mohamed Rahmouni ◽  
Julia Malysheva
Keyword(s):  
Navigation System ◽  
Attitude Determination ◽  
Recognition Algorithm ◽  
Integrated Navigation ◽  
Integration Algorithm ◽  
Integrated Navigation System ◽  
Aircraft Navigation ◽  
Horizon Line ◽  
Aircraft Motion ◽  
And Performance

An integration algorithm for a strapdown inertial navigation system with optical horizon sensor based on Kalman filtering is presented. It allows the accuracy of the estimation of aircraft motion parameters to be improved. A self-contained horizon recognition algorithm for the video sequence that enables real-time aircraft attitude determination relative to the horizon line is developed. A scaled-down simulation and performance analysis of the operation of the integrated navigation system is carried out.

Design of a low-cost attitude determination GPS/INS integrated navigation system

GPS Solutions ◽  
2005 ◽  
Vol 9 (4) ◽  
pp. 294-311 ◽  
Author(s):  
Dong-Hwan Hwang ◽  
Sang Heon Oh ◽  
Sang Jeong Lee ◽  
Chansik Park ◽  
Chris Rizos
Keyword(s):  
Navigation System ◽  
Attitude Determination ◽  
Low Cost ◽  
Integrated Navigation ◽  
Integrated Navigation System

scholarly journals Based on Grid Reference Frame for SINS/CNS Integrated Navigation System in the Polar Regions

Complexity ◽  
2019 ◽  
Vol 2019 ◽  
pp. 1-8 ◽  
Author(s):  
Song Lijun ◽  
Zhao Wanliang ◽  
Cheng Yuxiang ◽  
Chen Xiaozhen
Keyword(s):  
Reference Frame ◽  
Navigation System ◽  
Inertial Navigation System ◽  
Inertial Navigation ◽  
Polar Regions ◽  
Integrated Navigation ◽  
Integrated Navigation System ◽  
Celestial Navigation ◽  
Low Latitudes ◽  
And Performance

As the inertial navigation system cannot meet the precision requirements of global navigation in the special geographical environment of the Polar Regions, this paper presents Strapdown Inertial Navigation System (SINS)/Celestial Navigation System (CNS) integrated navigation system of airborne based on Grid Reference Frame (GRF) and the simulation is carried out. The result of simulation shows that the SINS/CNS integrated navigation system is superior to the single subsystem in precision and performance, which not only effectively inhibits the error caused by gyro drift but also corrects the navigation parameters of system without delay. Comparing the simulation in the middle and low latitudes and in the Polar Regions, the precision of SINS/CNS integrated navigation system is the same in the middle and low latitudes and in the Polar Regions.

scholarly journals SINS/Landmark Integrated Navigation Based on Landmark Attitude Determination

Sensors ◽  
2019 ◽  
Vol 19 (13) ◽  
pp. 2917
Author(s):  
Shuqing Xu ◽  
Haiyin Zhou ◽  
Jiongqi Wang ◽  
Zhangming He ◽  
Dayi Wang
Keyword(s):  
Navigation System ◽  
Inertial Navigation System ◽  
Attitude Determination ◽  
Feature Matching ◽  
Integrated Navigation ◽  
Basic Scheme ◽  
Integrated Navigation System ◽  
Celestial Navigation ◽  
Landmark Navigation ◽  
Navigation Method

Based on the situation that the traditional SINS (strapdown inertial navigation system)/CNS (celestial navigation system) integrated navigation system fails to realize all-day and all-weather navigation, this paper proposes a SINS/Landmark integrated navigation method based on landmark attitude determination to solve this problem. This integrated navigation system takes SINS as the basic scheme and uses landmark navigation to correct the error of SINS. The way of the attitude determination is to use the landmark information photographed by the landmark camera to complete feature matching. The principle of the landmark navigation and the process of attitude determination are discussed, and the feasibility of landmark attitude determination is analyzed, including the orthogonality of the attitude transform matrix, as well as the influences of the factors such as quantity and geometric position of landmarks. On this basis, the paper constructs the equations of the SINS/Landmark integrated navigation system, testifies the effectiveness of landmark attitude determination on the integrated navigation by Kalman filter, and improves the navigation precision of the system.

Multi-antenna GNSS and INS Integrated Position and Attitude Determination without Base Station for Land Vehicles

2018 ◽  
Vol 72 (2) ◽  
pp. 342-358 ◽  
Author(s):  
Xiaobo Cai ◽  
Houtse Hsu ◽  
Hua Chai ◽  
Leixiang Ding ◽  
Yong Wang
Keyword(s):  
Navigation System ◽  
Attitude Determination ◽  
Satellite System ◽  
Base Station ◽  
Integrated Navigation ◽  
Mobile Mapping ◽  
Integrated Navigation System ◽  
Yaw Angle ◽  
Mobile Mapping Systems ◽  
Mapping Systems

Precise Point Positioning/Inertial Navigation System (PPP/INS) integrated navigation based on PPP and low-accuracy INS is often used to provide position and attitude information for vehicle-mounted or airborne mobile mapping systems. With proper processing, the position accuracy of PPP/INS is comparable to that of Differential Global Navigation Satellite System (DGNSS)/INS, but the accuracy of the attitude, especially the yaw angle, cannot be guaranteed. However, the yaw angle is crucial for mobile mapping systems. To compensate for the insufficiency of PPP/INS, we have designed a Multi-Antenna GNSS (MAGNSS)/INS integrated navigation system. First, the attitude determination method using MAGNSS is presented in detail. Then, the MAGNSS attitude is combined with the PPP position and velocity as measurements for integration with the INS. Thus, PPP/INS integrated navigation was improved to MAGNSS/INS integrated navigation. Finally, a three-hour car-borne test was conducted to evaluate the performance of the proposed method. The results indicate that the attitude determined from MAGNSS is accurate and stable over time. Compared to PPP/INS, MAGNSS/INS integrated navigation can improve the attitude accuracy significantly because of the inclusion of MAGNSS attitude.

scholarly journals Performance analysis of GPS / Radar integrated navigation system

2019 ◽  
Vol 94 ◽  
pp. 02006
Author(s):  
Gwang Hee Jo ◽  
Jin Hyuk Lee ◽  
Jae Hee Noh ◽  
Ju Hyun Lee ◽  
Jae Min Ahn ◽  
...  
Keyword(s):  
Performance Analysis ◽  
Navigation System ◽  
Urban Canyon ◽  
Integrated Navigation ◽  
Radar Measurement ◽  
Integration Algorithm ◽  
Multipath Effect ◽  
Integrated Navigation System

GPS is used in various navigation fields. However, visibility is lowered in such an environment as urban canyon, and navigation performance deteriorates due to the visibility, multipath effect. So, in order to improve navigation performance in this environment, methods of integration with other sensors have been studied. In this paper, we use radar to measure the range of the landmark with known position. An integration algorithm is designed using GPS pseudorange and radar measurement.

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