High-performance INS/ADS And High Dynamic Of Virtual Simulation Technology

Compared with platform inertial navigation systems, the strapdown inertial navigation systemhas many advantages, such as small volume, light weight, low cost, and these characteristics are thedevelopment trend of inertial navigation systems. But the inertial navigation system is essentially awork based on the principle of an open-loop system. It needs a reference to assist navigationmeasurements, such as air data systems to suppress error divergent trends in inertial navigationsystems. With the improvement requirements of aircraft dynamic task, the study of the dynamiccharacteristics of the SINS has become more important. The approachhas based on virtual dynamicsimulation become an important means of comprehensive performance testing system.Because virtual simulation technology can saved the costs and shorten the cycle of systemdevelopment. This paper will be carried out a high-performance inertial/highly atmospheric anddynamic combination of virtual simulation technology research. It mainly consists of two parts virtualsimulation studies. There are the algorithm of the high-performance SINS/ADS damped and thealgorithm of the high-precision SINS algorithm and dynamic virtual simulation technology. Toprovides a theoretical basis of improving the performance of SINS height channels and increasing thedynamic simulation accuracy.For high maneuvers problem of high-performance SINS/ADS damping algorithm, we supposedthe improvement method of damping performance. This method can effectively meet the performancerequirements of non-stationary flight phase of the system, such as transonic phase. Because dampingalgorithm does not consider the estimation and compensation of atmospheric errors, the another studywas conducted. That is six-state Kalman filter methods of damping, which is through direct real-timeestimation and compensation of atmospheric height error amount, to improve the accuracy ofmeasurement of pressure altitude, and improved the accuracy of the vertical channel of SINS/ADSchannel ystem.Dynamic track is the basis for the research of SINS system. Due to the conventional flightsimulation algorithm ignores flight dynamics. The research on how to obtain a more realisticsimulation of aircraft flight parameters of dynamic data is of great significance. So the paperpresents three degrees of freedom track simulation algorithm based on model aircraft.In addition,there are differences between the dynamic track generation algorithm of aircraf dynamic model andSINS theory. Which will have a greater dynamic calculation error, this is a greater impact on thedynamic performance of the SINS. Therefore, the paper studies the SINS to achieve high-precisiondynamic simulation method to achieve the elimination of the dynamic calculation error. And to analyze different parameters of inertial sensor error model, the influence of the dynamic performanceof the SINS. For the selection of inertial sensors provides the basis theory.In basis studies of high-performance SINS/ADS combination of high and dynamic virtualsimulation, we designed the virtual test system software and achieved the sthudy of high-performanceSINS/ADS combination of high and dynamic virtual simulation. For the engineered of the systemprovides effective support.