Launch Vehicle Fault-tolerant Navigation Filter And Applying Research

The launch vehicle is currently the most widely used means of transport ofspace. With the development of aerospace technology; the use and development ofspace resources are more and more extensive. This has the urgent needs of low-costlaunch vehicle R&D and manufacturing. Especially for our country, in recent yearschina has a large amount of space missions, The implementation of "Compass II"navigation system and "Chang E Project" put forward ever-increasing demands ofLow-cost, highly reliable launch vehicle research and developmentNavigation system as one of the major systems of the launch vehicle toundertake the task of guided rocket accurately entered its orbit, precise navigationdata is the basis of the launch vehicle guidance and control systems work properly.Effective development of low cost and highly reliable navigation system will reducelaunch vehicle development costs and improve system reliability.According to analysis of launch vehicle flight environment features andsophisticated navigation technology at home and abroad, In this paper, the launchvehicle navigation system design is a combination of redundancy SIMU and globalnavigation positioning system (GPS).The program not only under the premise ofensuring navigation and positioning accuracy, but also avoid platform inertialnavigation system to the structure of heavy, bulky and expensive problem.This paper builds the launch vehicle dynamics and kinematics of the sixdegrees of freedom mathematical model, introduces the principle of strapdowninertial navigation systems and GPS navigation system, and give the navigationsolution method. On the basis of analysis of the launch vehicle flight environmentcharacteristics，the principle of inertial navigation and GPS navigation principle,failure mode model of strapdown inertial navigation systems and GPS navigationsystems are being built. In the same time, examine the Redundant InertialMeasurement Unit’s measurement data, which is using direct comparison of themeasured value method and parity method. It improves the reliability of the inertialnavigation system, reduces the reliability of single inertial measurement unitrequirements, and ensures the navigation accuracy and reliability of navigationsystems under the premise of effectively reducing the development cost of thenavigation system. Using fault-tolerant integrated navigation filter based on Kalman filteringtheory and particle filter theory to effectively deal the navigation data of inertialnavigation systems and GPS. SINS/GPS fault-tolerant integrated navigation systemmodel is being build. The use of high navigation and positioning accuracy and doesnot drift with time characteristics of GPS navigation to correct the cumulative errorof strapdown inertial navigation system. It reduces the measurement accuracyrequirements of the inertial navigation system, improves the fault tolerance abilityof navigation system and effectively reduces the cost of the navigation system,improves the reliability of the navigation system. This paper provides a referencefor development of low-cost, highly reliable launch vehicle navigation systems.