The Design And Instrumentation Of Intergrated Navigation System Of Landform Survey Vehicle

Landform survey vehicle is one of main equipment,which is composed of modern airdefense system,it mainly provide position terrain information,location information and guidweapon systerm.Among the Composition of Landform survey vehicle,Navigation system ismainly used for measuring vehicle’s three-dimensional position information andthree-dimensional posture information.At present,Navigation system is used the most,otheraided navigation system include GPS navigation system,dead reckoning system,mapmatching system etc.Landform survey vehicle require high on navigation precision,rapidstart-up,system redundancy and system reliability,along with the a new inertial componentsappear,navigation precision has been improved a lot,but single navigation system is difficultto satisfy all the requirements of Landform survey vehicle.So it has significance for us tomake the systerm,which has higher navigation precision and shorter alignment time but alsohas low manufacturing cost.This paper first introduces Current research status of domestic and internationalintegrated navigation system for vehicle and fiber optic gyroscope,then lists the basic workingprinciple of the fiber optic gyroscope,GPS,odometer. Through the comparison of platforminertial navigation system and inertial navigation system,and combine with the thirdgeneration of Landform survey vehicle system requirements,selection of fiber optic gyroreplaced traditional mechanical gyroscope,at the same time to reduce the system’s cost andminiaturization of the system requirements,finally we select the strapdown inertial navigationsystem.Then,introduces optical fiber gyro and accelerometer’s mainly error source,combine withthe basis working principle,finally has established the mathematical error model.According tothe mathematical model’s characteristics,we have designed experiment, through dataprocessing,finally we obtain gyroscope and accelerometer mathematical error model.According to the system’s requirement,the alignment time and alignment accuracy havehigher requirements.we achieve the static base condition of coarse alignment,then refineinitial alignment using Kalman filtering.In the design of Kalman filter process,we detail andestablish the error model of the SINS which ued in the paper.Finally,Designed two kinds of Integrated Navigation Systems.Through the simulationexperiment, validate the filter’s performance.