Adaptive neuro-fuzzy module for inertial navigation system/global positioning system integration utilising position and velocity updates with real-time cross-validation

2007 ◽  
Vol 1 (5) ◽  
pp. 388 ◽  
Author(s):  
A. Noureldin ◽  
A. El-Shafie ◽  
N. El-Sheimy
Keyword(s):  
Real Time ◽  
Global Positioning System ◽  
Navigation System ◽  
System Integration ◽  
Inertial Navigation System ◽  
Cross Validation ◽  
Inertial Navigation ◽  
Positioning System ◽  
Neuro Fuzzy ◽  
Global Positioning

Auto Takeoff and Precision Terminal-Phase Landing Using an Experimental Optical Flow Model for Global Positioning System/Inertial Navigation System Enhancement

2018 ◽  
Vol 5 (1) ◽  
Author(s):  
Mohammad K. Al-Sharman ◽  
Mohammad Amin Al-Jarrah ◽  
Mamoun Abdel-Hafez
Keyword(s):  
Optical Flow ◽  
Real Time ◽  
Global Positioning System ◽  
Navigation System ◽  
Inertial Navigation System ◽  
Inertial Navigation ◽  
Position Error ◽  
Positioning System ◽  
The Real ◽  
Global Positioning

The high estimated position error in current commercial-off-the-shelf (GPS/INS) impedes achieving precise autonomous takeoff and landing (TOL) flight operations. To overcome this problem, in this paper, we propose an integrated global positioning system (GPS)/inertial navigation system (INS)/optical flow (OF) solution in which the OF provides an accurate augmentation to the GPS/INS. To ensure accurate and robust OF augmentation, we have used a robust modeling method to estimate OF based on a set of real-time experiments conducted under various simulated helicopter-landing scenarios. Knowing that the accuracy of the OF measurements is dependent on the accuracy of the height measurements, we have developed a real-time testing environment to model and validate the obtained dynamic OF model at various heights. The performance of the obtained OF model matches the real OF sensor with 87.70% fitting accuracy. An accuracy of 0.006 m/s mean error between the real OF sensor velocity and the velocity of the OF model is also achieved. The velocity measurements of the obtained OF model and the position of the GPS/INS are used in performing a dynamic model-based sensor fusion algorithm. In the proposed solution, the OF sensor is engaged when the vehicle approaches a landing spot that is equipped with a predefined landing pattern. The proposed solution has succeeded in performing a helicopter auto TOL with a maximum position error of 27 cm.

The Design of INS under PBN

2013 ◽  
Vol 336-338 ◽  
pp. 1028-1031
Author(s):  
Ming Qiang Chen
Keyword(s):  
Mechanical Properties ◽  
Global Positioning System ◽  
Navigation System ◽  
Mechanical Engineering ◽  
Inertial Navigation System ◽  
Inertial Navigation ◽  
Civil Aviation ◽  
Positioning System ◽  
Global Positioning

The Global Positioning System (GPS) has been approved for a limited number of applications in civil aviation because it is not highly available for meeting safety-of life levels of integrity, which require timely alert if the system is unreliable for navigation under the environment of Performance Based on Navigation (PBN). This paper presents an analysis about principle of an inertial navigation system (INS) and design an new mechanical architecture of INS in terms of increased availability of GPS for civil aviation. This new mechanical architecture has a good mechanical properties in mechanical engineering of civil aviation.

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