Relative Navigation Methods Of Flying Formation In Large Ellipitical Orbit Based On Angles-only Information

Relative navigation technology is one of the key technologies of formation flying technology throughout the development,design,and practical application.This dissertation studies the angles-only relative navigation,based on large elliptic orbit and formation flying.In traditional all measurement information process of the relative navigation filter,the large number of measuring sensors with huge volume are not suitable for small aircraft flight formation.Once payload lose efficacy,they can't repair.Compared with the all measurement information of relative navigation system,the angles-only relative navigation lacks the distance information.This dissertation mainly does qualitative analysis on observability of angles-only relative navigation system;in the side of quantity analysis,this dissertation uses a revised singular value decomposition(SVD)method.To solve the problem of lack of "relative distance information" and weak observability,this dissertation uses conducting orbit maneuver for distance information scheme and measuring more sights scheme which are practical.The contents of this dissertation mainly include the following aspects.Establish the dynamics T-H equations of relative motion between spacecrafts and the formula of linear Kalman filtering algorithm process is given.Establish measurement models of all measurement information and angles-only relative navigation system in measuring coordinate system of chasers;deduce Jacobian matrixes which apply to Kalman filtering.This paper gives the observability definition of the angles-only relative navigation system based on discrete time-varying systems;uses a revised singular value decomposition(SVD)method to make quantitative analysis.Comparing mathematical simulation of two relative navigation systems,the observability and navigation accuracy of angles-only relative navigation system are far below the all measurement information system.Go into more detail on orbital maneuver to get distance information and solve the problem of weak observability.The Bernoulli distribution describes the phenomenon of discontinuous distance information and measurement data lack.The robust Kalman filtering based on Huber estimation is used.The simulation results show that navigation accuracy is reasonable and scheme is feasible.The scheme of measuring more sights can carry out relative state estimation.Analyse the observability of relative navigation system based on stable configuration of triangle.Combined with extended Kalman filter,distributed data processing can solve the problems of much measuring information and calculating high dimension matrixes.The main chaser and aided chaser cooperate with each other to complete the navigation filter.The mathematical simulation results show that navigation accuracy is reasonable and scheme is feasible.For uncertain models with unknown maneuvering acceleration,a MMAE filtering algorithm adapted to multi sight measurement is adopted...