1974 TEST OF LACOSTE AND ROMBERG INERTIAL NAVIGATION SYSTEM

Geophysics ◽  
1977 ◽  
Vol 42 (3) ◽  
pp. 594-601 ◽  
Author(s):  
Lucien J. B. LaCoste
Keyword(s):  
Gulf Of Mexico ◽  
Navigation System ◽  
Inertial Navigation System ◽  
Inertial Navigation ◽  
Satellite Navigation ◽  
The Other ◽  
Inertial System ◽  
Oil Exploration ◽  
Satellite Information ◽  
Made In

In mid-1974 a test was made in the Gulf of Mexico of a LaCoste and Romberg inertial system for the measurement of the Eötvös correction for shipboard gravity meters. Since the system is designed for operation with satellite navigation, inertial velocities were updated at 2- to 3-hour intervals, using Lorac information because no satellite information was available. Two types of comparison were made between the inertial and Lorac data. One comparison was the rms difference between results from the two methods—0.46 knot, which corresponds to 3.0 mgal at a latitude of 30 degrees. The other comparison related to noise which could be mistaken for anomalies of interest in oil exploration. The comparison indicated that such noise in the inertial data was only about one third that in the Lorac data.

Research and Analysis of Accuracy of Location Estimation in Inertial Navigation System

2016 ◽  
Vol 817 ◽  
pp. 308-316 ◽  
Author(s):  
Piotr Rajchowski ◽  
Krzysztof Cwalina ◽  
Jarosław Sadowski
Keyword(s):  
Navigation System ◽  
Indoor Environment ◽  
Inertial Navigation System ◽  
Inertial Navigation ◽  
Digital Signal ◽  
Location Estimation ◽  
Navigation Algorithms ◽  
Movement Parameters ◽  
Measuring Unit ◽  
Made In

In the article the research and analysis of digital signal processing and its influence on accuracy of location estimation in developed inertial navigation system was presented. The purpose of the system is to localize moving people in indoor environment. During research a measuring unit for recording selected movement parameters was made. In the article were also described author’s inertial navigation algorithms.

scholarly journals Landmark-Based Inertial Navigation System for Autonomous Navigation of Missile Platform

Sensors ◽  
2020 ◽  
Vol 20 (11) ◽  
pp. 3083
Author(s):  
Donghui Lyu ◽  
Jiongqi Wang ◽  
Zhangming He ◽  
Yuyun Chen ◽  
Bowen Hou
Keyword(s):  
Navigation System ◽  
Autonomous Navigation ◽  
Inertial Navigation System ◽  
Attitude Determination ◽  
Inertial Navigation ◽  
Inertial System ◽  
New Information ◽  
System Output ◽  
Navigation Method ◽  
Navigation Scheme

As a new information provider of autonomous navigation, the on-orbit landmark observation offers a new means to improve the accuracy of autonomous positioning and attitude determination. A novel autonomous navigation method based on the landmark observation and the inertial system is designed to achieve the high-accuracy estimation of the missile platform state. In the proposed method, the navigation scheme is constructed first. The implicit observation equation about the deviation of the inertial system output is derived and the Kalman filter is applied to estimate the missile platform state. Moreover, the physical observability of the landmark and the mathematical observability of the navigation system are analyzed. Finally, advantages of the proposed autonomous navigation method are demonstrated through simulations compared with the traditional celestial-inertial navigation system and the deeply integrated celestial-inertial navigation system.

Researching of the low-precision SINS research for an unmanned vehicle

2020 ◽  
Keyword(s):  
Navigation System ◽  
Inertial Navigation System ◽  
Adaptive Estimation ◽  
Inertial Navigation ◽  
Estimation Algorithm ◽  
Satellite Navigation ◽  
Accuracy Class ◽  
Unmanned Vehicle ◽  
Satellite Navigation System ◽  
Algorithmic Support

A small-sized inertial navigation system (SINS) Gyrolab GL VG 109 is researched. It is shown that this system has low accuracy; therefore it cannot be used to determine the parameters of an unmanned vehicle in an autonomous mode. Correction of the system from the satellite navigation system significantly increases the accuracy of determining the parameters of an unmanned vehicle, but only under conditions of stable signals from the satellite navigation system (SNS). The algorithmic support for the correction facility of the navigation system based on the scalar adaptive estimation algorithm and identification procedure is formed. The use of algorithmic correction of SINS from SNS using an estimation algorithm allows achieving an accuracy that corresponds to systems of the third accuracy class. Keywords inertial navigation system without platform; unmanned vehicle; correction; satellite navigation system; scalar estimation algorithm; scalar identification; analysis of accuracy

scholarly journals The Stabilized Radiometer Platform (STRAP)—An Actively Stabilized Horizontally Level Platform for Improved Aircraft Irradiance Measurements

2008 ◽  
Vol 25 (12) ◽  
pp. 2161-2175 ◽  
Author(s):  
Anthony Bucholtz ◽  
Robert T. Bluth ◽  
Ben Kelly ◽  
Scott Taylor ◽  
Keir Batson ◽  
...  
Keyword(s):  
Navigation System ◽  
Solar Irradiance ◽  
Inertial Navigation System ◽  
Inertial Navigation ◽  
The Other ◽  
Identical Pair ◽  
Update Rate

Abstract Measurements of solar and infrared irradiance by instruments rigidly mounted to an aircraft have historically been plagued by the introduction of offsets and fluctuations into the data that are solely due to the pitch and roll movements of the aircraft. The Stabilized Radiometer Platform (STRAP) was developed to address this problem. Mounted on top of an aircraft and utilizing a self-contained, coupled Inertial Navigation System–GPS, STRAP actively keeps a set of uplooking radiometers horizontally level to within ±0.02° for aircraft pitch and roll angles of up to approximately ±10°. The system update rate of 100 Hz compensates for most pitch and roll changes experienced in normal flight and in turbulence. STRAP was mounted on a Twin Otter aircraft and its performance evaluated during normal flight and during a series of flight maneuvers designed to test the accuracy, range, and robustness of the platform. The measurements from an identical pair of solar pyranometers—one mounted on STRAP and the other rigidly mounted nearby directly to the aircraft—are compared to illustrate the accuracy and capability of the new platform. Results show that STRAP can keep radiometers level within the specified pitch and roll range, that it is able to recover from flight maneuvers outside of this range, and that it greatly increases the quantity of useful radiometer data from any given flight. Of particular note, STRAP now allows accurate measurements of the downwelling solar irradiance during spiral ascents or descents of the aircraft, greatly expanding the utility of aircraft radiometer measurements.

High-Precision Kinematic Satellite and Doppler Aided Inertial Navigation System

2010 ◽  
Vol 64 (1) ◽  
pp. 91-108 ◽  
Author(s):  
Ranjan Vepa ◽  
Amzari Zhahir
Keyword(s):  
High Precision ◽  
Navigation System ◽  
Carrier Phase ◽  
Inertial Navigation System ◽  
Unscented Kalman Filter ◽  
Inertial Navigation ◽  
Satellite Navigation ◽  
Initial Alignment ◽  
Phase Measurements ◽  
Satellite Navigation System

In this paper an adaptive unscented Kalman filter based mixing filter is used to develop a high-precision kinematic satellite aided inertial navigation system with a modern receiver that incorporates carrier phase smoothing and ambiguity resolution. Using carrier phase measurements with multiple antennas, in addition to a set of typical pseudo-range estimates that can be obtained from a satellite navigation system such as GPS or GLONASS, the feasibility of generating high precision estimates of the typical outputs from an inertial navigation system is demonstrated. The methodology may be developed as a stand-alone system or employed in conjunction with a traditional strapped down inertial navigation system for purposes of initial alignment. Moreover the feasibility of employing adaptive mixing facilitates the possibility of using the system in an interoperable fashion with satellite navigation measurements.

GNSS/IMU integration algorithm experimental evaluation

2021 ◽  
pp. 52-64
Author(s):  
I.A. Nagin ◽  
A.Yu. Shatilov ◽  
T.A. Muhamedzyanov ◽  
Yu.M. Inchagov
Keyword(s):  
Navigation System ◽  
Experimental Evaluation ◽  
Inertial Navigation System ◽  
Inertial Navigation ◽  
Satellite Navigation ◽  
Integration Algorithm ◽  
Satellite Navigation System ◽  
Navigation Solution ◽  
Inertial Measuring Unit ◽  
Measuring Unit

To improve the reliability and accuracy of navigation solution, the integration of the satellite navigation receiver with the inertial navigation system is used. These systems have complementary characteristics. An important part of the combined systems is the integration algorithm, which largely determines the final characteristics. The synthesis of such an algorithm for velocity, attitude and the errors of the inertial measuring unit estimation has been carried out. The algorithm is implemented in the software of the prototype of the inertial-satellite navigation system. The results of the experimental evaluation of algorithm’s characteristics for automotive dynamics are shown.

scholarly journals MEASUREMENT AND ESTIMATION OF THE ANGLE OF ATTACK AND THE ANGLE OF SIDESLIP

Aviation ◽  
2015 ◽  
Vol 19 (1) ◽  
pp. 19-24 ◽  
Author(s):  
Stanisław Popowski ◽  
Witold Dąbrowski
Keyword(s):  
Navigation System ◽  
Velocity Measurement ◽  
Inertial Navigation System ◽  
Angle Of Attack ◽  
Inertial Navigation ◽  
Satellite Navigation ◽  
Linear Velocity ◽  
Estimation Methods ◽  
Satellite Navigation System ◽  
Sideslip Estimation

The paper presents issues concerning the estimation of the angle of attack and the angle of sideslip on a flying object board. Angle of attack and sideslip estimation methods which are based on measurements of linear velocity components of an object with the Earth’s coordinates and on attitude angles of the object are presented. Both of these measurements originate from the inertial navigation system, and velocity measurement is obtained from the satellite navigation system. The idea of applying inertial and satellite navigation for the estimation of attack and sideslip angles is presented. Practical comparison of these estimation methods has been conducted based on logged parameters of a flight onboard a Mewa aircraft. Development proposals for these methods are presented as well.

scholarly journals Compensation for errors in determining the angle in the flight-navigation complex of the aircraft in case of failure of the satellite navigation system

2019 ◽  
Vol 11 (S) ◽  
pp. 7-16
Author(s):  
Eugeni V. AKIMOV ◽  
Dmitriy M. KRUZHKOV ◽  
Vyacheslav A. YAKIMENKO
Keyword(s):  
Navigation System ◽  
Inertial Navigation System ◽  
Inertial Navigation ◽  
Satellite Navigation ◽  
Ground Speed ◽  
Satellite Navigation System ◽  
Long Duration ◽  
Definition Of ◽  
Navigation Equipment ◽  
Navigation Information

Currently, navigation equipment for long-range aircraft, where the flight is characterized by a long duration and the absence of frequent and abrupt maneuvers, continues to be actively improved. Therefore, the main purpose of the work is to analyze the compensation of the error in determining the angle in the flight-navigation complex of the aircraft in case of failure of the satellite navigation system. In order to achieve the goal, inertial navigation methods using an attitude and heading reference system were used. It was determined that when comparing the evolution graphs of the heading and errors in determining the eastern component of the ground speed, it is possible to establish the dependence that at the moments of maneuvers associated with a significant change in the direction of this speed, the phase and amplitude of the error fluctuations are also changed. It was established that today the operational technology is equipped with blocks of an inertial navigation system. It helps to improve the accuracy of the definition of navigation information.

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