Inertial/Satellite GNC Systems for Space Launchers: Theory and Results of the First Realized Missions
Radio engineering. Electronics. Telecommunication systems
AbstractThe new approach to formation of redundancy of satellite measurements and to statistical treatment of these measurements in the problems of dynamic filtration is presented. This approach is directed towards the use in integrated GNC systems for dynamic objects the guidance of which is a process of irreversible nature. On the basis of the influence function theory, the analytic dependences of estimation errors upon inertial and noninertial measurements errors, dynamic disturbances, and various setting parameters are obtained. The interrelation of estimations obtained on the basis of the proposed approach and in terms of the Kalman filter is shown. The theoretical results laid the groundwork for the new version of the dynamic filtration method that served as a basis for the onboard software of the integrated inertial/satellite GNC systems for space launchers. The results of the first applications of that sort of systems during Fregat upper stage missions (injections of Meteor-M, Globalstar-2, and Electro-L satellites) are discussed.
Keywords:satellite and inertial navigation; terminal guidance; conjugate system; flight test