Certification Flight Test Methods for Pilot and Navigation Systems Using the Integrated System Based on Satellite Technologies

Author(s):  
Evgeniy Kharin ◽  
Anatoliy Yakushev ◽  
Oleg Mordvinov ◽  
Vladivir Kopelovitch ◽  
Lavrentiy Lovitskiy ◽  
...  
Sensors ◽  
2021 ◽  
Vol 21 (9) ◽  
pp. 2922
Author(s):  
Fan Zhang ◽  
Ye Wang ◽  
Yanbin Gao

Fault detection and identification are vital for guaranteeing the precision and reliability of tightly coupled inertial navigation system (INS)/global navigation satellite system (GNSS)-integrated navigation systems. A variance shift outlier model (VSOM) was employed to detect faults in the raw pseudo-range data in this paper. The measurements were partially excluded or included in the estimation process depending on the size of the associated shift in the variance. As an objective measure, likelihood ratio and score test statistics were used to determine whether the measurements inflated variance and were deemed to be faulty. The VSOM is appealing because the down-weighting of faulty measurements with the proper weighting factors in the analysis automatically becomes part of the estimation procedure instead of deletion. A parametric bootstrap procedure for significance assessment and multiple testing to identify faults in the VSOM is proposed. The results show that VSOM was validated through field tests, and it works well when single or multiple faults exist in GNSS measurements.


1995 ◽  
Vol 48 (2) ◽  
pp. 293-302 ◽  
Author(s):  
Allison N. Ramjattan ◽  
Paul A. Cross

Unlike in the case of airborne and offshore applications, GPS cannot be used continuously for land vehicle navigation due to the loss of satellite signals by obstructions from buildings, trees, etc. With the increasing trend in various sectors of the economy towards efficient fleet management, the challenges of providing a system capable of providing high-accuracy vehicle position and location anywhere, continuously, has led to renewed interest in the area of integrated navigation systems. In order to satisfy these conditions, an integrated system comprising GPS and gyro/odometer dead reckoning has been developed. This paper gives a description of the implemented system and shows some of the practical results that can be obtained using Kalman filtering algorithms.


2014 ◽  
Vol 67 (6) ◽  
pp. 967-983 ◽  
Author(s):  
Zengke Li ◽  
Jian Wang ◽  
Binghao Li ◽  
Jingxiang Gao ◽  
Xinglong Tan

The integration of Global Positioning Systems (GPS) with Inertial Navigation Systems (INS) has been very actively studied and widely applied for many years. Some sensors and artificial intelligence methods have been applied to handle GPS outages in GPS/INS integrated navigation. However, the integrated system using the above method still results in seriously degraded navigation solutions over long GPS outages. To deal with the problem, this paper presents a GPS/INS/odometer integrated system using a fuzzy neural network (FNN) for land vehicle navigation applications. Provided that the measurement type of GPS and odometer is the same, the topology of a FNN used in a GPS/INS/odometer integrated system is constructed. The information from GPS, odometer and IMU is input into a FNN system for network training during signal availability, while the FNN model receives the observations from IMU and odometer to generate odometer velocity correction to enhance resolution accuracy over long GPS outages. An actual experiment was performed to validate the new algorithm. The results indicate that the proposed method can improve the position, velocity and attitude accuracy of the integrated system, especially the position parameters, over long GPS outages.


2013 ◽  
Vol 748 ◽  
pp. 747-753 ◽  
Author(s):  
Dan Wang ◽  
Wei Wang

It is a very difficult task to land on aircraft carrier, because of limits of the carrier runway during rough sea. In this article, a new algorithm of aircraft carrier landing is proposed utilizing airborne infrared camera/inertial integrated system, which can provide the relative positions and orientation of the aircraft with respect to the carrier so as to help aircrafts semi-auto or auto landing. The mathematic relationship between guidance parameters and imaging information was modeled, and then the relative position and attitude information between the carrier and the aircraft were estimated through Newton iteration method. From that information, the pitching, rolling and heave movement of the carrier were estimated and compensated, so the touchdown point could be predicted and provided to the pilot so as to control aircraft landing. On the ground of the theoretic research, the field verification tests were carried out, which adopted the minification scheme to simulate the process of aircraft carrier landing. In the experiments, the runway simulator simulated the motion of the carrier runway and the land vehicle was used as the aircraft. The results verify the landing guidance system scheme is feasible and effective, and lay the technical foundation for the flight test, improving its safety.


2012 ◽  
Vol 433-440 ◽  
pp. 4065-4070
Author(s):  
Qiang Gao ◽  
Shan Jin ◽  
Tie Liu Wang

The GPS / INS integrated navigation system performance will significantly decrease during GPS outages. In this paper, we study an new integrated navigation algorithm based on Adaptive Neural- fuzzy Inference System (ANFIS). The algorithm adopted Kalman filter with pseudo-range and pseudo-range rate observations when the number of GPS satellites was not less 4. Otherwise, ANFIS was used to estimate the navigation errors and restrain the increasing INS errors to achieve integrated navigation. The new algorithm can improve the performance of integrated system effectively and enhance the horizontal position accuracy than traditional tight integration algorithms. Especially, the method is applicable to the complex work environment of navigation systems of ships.


2013 ◽  
Vol 347-350 ◽  
pp. 1544-1548
Author(s):  
Zi Yu Li ◽  
Yan Liu ◽  
Ping Zhu ◽  
Cheng Ying

In multi-sensor integrated navigation systems, when sub-systems are non-linear and with Gaussian noise, the federated Kalman filter commonly used generates large error or even failure when estimating the global fusion state. This paper, taking JIDS/SINS/GPS integrated navigation system as example, proposes a federated particle filter technology to solve problems above. This technology, combining the particle filter with the federated Kalman filter, can be applied to non-linear non-Gaussian integrated system. It is proved effective in information fusion algorithm by simulated application, where the navigation information gets well fused.


Sign in / Sign up

Export Citation Format

Share Document