The Error Compensation Technology Of Aircraft Navigation System

With the requirements of modern military aircraft navigation accuracy,aircraft navigation systems often use two or more navigation systems for navigation.Currently,the Strap-down Inertial Navigation System(SINS)and Global Positioning System(GPS)is the most commonly two aircraft navigation systems.SINS does not need the outside world to provide information,at the same time without interference from the external environment,but its own inertia component errors increase over time accumulate.Its long-term accuracy is poor.GPS can provide positioning information around the clock,and its positioning errors does not increase over time accumulate.GPS can guarantee long-term precision of navigation,but the existence of anti-interference ability is poor.There is also multi-path effects and other issues too GPS.The combination of two navigation systems as the aircraft navigation system,to complement each other,the navigation system could has higher performance.This article adopts SINS/GPS tightly integrated system as aircraft navigation system,and conduct its tightly integrated system error analysis system and to achieve compensation,so that the aircraft navigation system could achieve higher performance.First of all,this article provides an overview of strapdown inertial navigation system and error analysis of high dynamic strapdown inertial navigation system.Meanwhile,completing strap-down inertial navigation system simulation,including trajectory generation,inertial component simulation and strap-down inertial navigation solver simulation.Secondly,this article introduces the composition and positioning principles of the GPS,and analyzes the error of the global positioning system.Meanwhile,this article introduces the solving the details of satellite real-time position and velocity information,and accomplishs the simulation of an improved algorithm for SINS assisted GPS selecting stars.Finally,based on error analysis of strap-down inertial navigation system and global positioning system,this article builds equation of the high dynamic system state.This article builds systems measurement equation by chooseing the SINS and GPS navigation information as measurement,and achieve error compensation by Kalman filtering algorithm.According to the conventional Kalman filter divergent problems,this article selectes a method,which can be effectively suppressed divergent by using Sage-Husa adaptive filtering method.By MATLAB simulation,it can effectively reduce navigation errors of aircraft navigation system compared to the conventional Kalman filter.