Research On The Comprehensive Processing Method Of Integrated Navigation Information Of Civil Passenger Aircraft

In the twenty years since entering the new century,the global aviation industry has ushered in a blowout development,the surge of air transport business to promote the global demand for air transport continues to increase,the civil aviation industry presents a thriving development trend,a variety of new technologies and new means emerge in an endless stream.Navigation system,as the eyes of the aircraft,is undoubtedly one of the most important components of the aircraft system The Strap-down Inertial Navigation System(SINS)with high accuracy in a short time,susceptible to interference,data output is complete,and high frequency in a short period of time have become essential navigation systems for airborne navigation,but there are some disadvantages such as error accumulation over time and high cost of high precision inertial navigation unit.Global positioning system(GPS)has the advantages of high accuracy and good reliability.The accuracy of integrated navigation and positioning can be improved by correcting the GPS position and speed information to the inertial navigation output.Therefore,combining the two approaches is the most ideal navigation solution.In order to explore the feasibility of integrated navigation information processing method,this paper proposes a method to simulate the real flight track by using integrated navigation information processing method.At the same time,the error characteristics of airborne inertial navigation devices are simply studied,and the numerical level of the influence of component error and motion interference error on the airborne inertial navigation device error during the flight is obtained.The main research contents in this article are as follows: Firstly,a detailed analysis of the SINS and the global navigation positioning system.The common coordinate system and its mutual conversion relationship in the five combinations were detailed and analyzed the working principles,update principles and sources of error sources,and an error model was established.Ten error sources of the strap-down inertial navigation system are analyzed,the basic principles of the two positioning methods of the global positioning system are studied,and the main error sources are studied and the corresponding correction scheme is given.The Kalman filter algorithm,then the key technology of the information processing of the combination navigation.system.Then,the integrated of the SINS/GPS pine combination is used to combine the speed and location information of the vehicle carrier records to verify the theory of the Integrated navigation accuracy higher than the single SINS navigation accuracy.Finally,a real test flight data was combed to combine the flight process,and two representative two stage trajectory data were selected to simulate the track of the track.Optimized the drawing traces is closer to the real flight trail and higher accuracy.On this basis,the component errors and motion error characteristics of the carrier navigation are also briefly studied.The validity of the comprehensive processing method of integrated navigation information has been verified,and it has certain reference significance for the actual civil aviation operation.