Research On Airborne Autonomous Integrity Monitoring For Aircraft Approach And Landing And Muti-constraint Attitude Determination Methods With Muti-antenna

Taking the approach and landing of the aircraft as the background and aiming to meet the requirements of high precision and high integrity,this dissertation proposes a preliminary design to the overall plan of the approach and landing system which is based on the satellite navigation system and studies the key technologies related with close distance of the process including airborne autonomous integrity monitoring and multi-constraint attitude determination method with multi-antenna.According to the requirement of high precision and high integrity position in the task,this dissertation carries out the the research on the multiple hypothesis solution separation method(MHSS)for carrier phase and INS-aided cycleslip integrity monitoring method.Most of the widespread receiver autonomous integrity monitoring methods focuses on the undifferenced pseudorange observations at the present.This dissertation extends the basic methods for pseudorange to double-differenced carrier phase observations.Developed for the integrity monitoring of multi-frequency pseudorange observations of multi-constellation,MHSS can detect multiple faults and gradually have the exclusion fuctions,which is considered as the typical representativeness of the next generation integrity monitoring method.This dissertation applies MHSS to carrier phase observations for the first time with a detailed introduction of its basic theory and proposes a new method to calculate positioning error protect level which can improve the calculation accuracy obviously.Afterwards,the model applicability is verified by the measured data from static test and the feasibility and validity of the methods are proved by the comparison of the results of the standard receiver autonomous integrity monitoring method and MHSS for carrier phase observations under the condition of fault free and inserted faults.INS-aided cycleslip integrity monitoring method constructs the test statistics with the positon difference between epoches provided by inertial navigation system and produce the decision threshold by the required continuity risk.Three test statistics are used in this method to get a complementary advantage which causes to a stronger ability of detection.Besides,the decision threshold is produced by the required continuity risk which is different from the traditional methods produced according to experience.The feasibility and validity of the methods are proved by the comparison of the results of the traditional methods and INS-aided cycleslip integrity monitoring method based on the measured data from static test.According to the requirement of high precision attitude in the task,this dissertation carries out the the research on the multi-constraint attitude determination method with multi-antenna.This method extends the traditional attitude determination model to an original model based on attitude matrix using the elements of the attitude matrix as the unknown parameters.Therefore,with this change the prior information of the length and intersection angle of the baselines turns into the orthogonal constraint of the attitude matrix,which can be beneficial to the carrier integer resolution,attitude estimation and baseline estimation and the number of geometrical constraints dose not increase with the number of baselines.And the linearization of the nonlinear constraint iteration method is proposed to determine the orthogonal attitude matrix.Static Test results of three antennas based on observation data from the BDS show that this new model and algorithm are practical workable and can reduce the fixed time of the carrier integer,increase the single epoch fixed rate and improve the estimation accuracy of attitude and baselines apparently compared with the traditional method.The second generation Beidou Satellite Navigation System which is constructed and researched independently by our country has been put into use,the research in this dissertation can provide technological support for the realization of the secure landing for aircraft in foul-weather conditions and give the research ideas and theoretical basis for our own automatic landing system based on satellite navigation system.