Research On Navigation Technology Of Pulsar Observation Under Multi Mode

Pulsars are a unique class of neutron stars that spin rapidly and stably,being of super-nuclear density,strong electro-magnetic field and strong gravitational field.They have been broadly used in the study on celestial body's evolution,gravitational wave detection and many other frontiers.Compared to the satellite navigation system and the earth-based tracking network which have restrictions of huge maintenance cost,coverage area limitation and lower safety,pulsars navigation can provide autonomous,safe,precise and high price-performance ratio properties,so studying on pulsar navigation not only is of important value in military,but also can suit the demand in deep space detectionThis article takes X-ray pulsar for research object,study the related work of positioning and aligning based on the pulsar observation.The specific work is as follows:(1)According to the characteristics of pulsar period with high stability,on the basis of satellite navigation,celestial navigation mode,study the location algorithm based on X-ray pulsar timing observation.In the case of the approximate location of the spacecraft,try to research error iterative algorithm to achieve a higher accuracy;In the case of unknown spacecraft location optimization,integer ambiguity traversal methods,study absolute positioning of spacecraft.(2)Under the premise of organizing necessary basic knowledge of polarization orientation,The whole process of the pulsar's attitude algorithm is presented.First of all,we study the method of polarization observation of pulsar,and get the information of polarization observation;next,the stability factor is quoted to capture the polarization information and find the optimal polarization view.The simulation results show that the optimal polarization information is at the peak of the pulse;finally,the navigation algorithm based on polarization information is presented and the feasibility of the simulation is verified.In the aspect of positioning based on the observation of pulsar timing,assuming the internal clock of the spacecraft can be considered stable enough to be a valid reference and a previous coarse knowledge of the spacecraft position is acquired.By observing the 4 long periods of pulsar,we simulate the absolute positioning simulation in two cases of spacecraft stationary.The simulation results show that the algorithm can achieve the satellite positioning and the positioning accuracy can be achieved by selecting the appropriate threshold without considering the relative correction.In the aspect of attitude determination based on polarization observations of Pulsars,assuming the initial deviation is given and only considered observation noise and model noise are considered,Simulate the spacecraft under static conditions,discuss the feasibility of attitude solution by using polarization attitude algorithm.The simulation results show that the method is feasible,and the accuracy of the fixed position can reach 0.04 degrees in theory.