Research On Satellite Positioning And Control Technology Based On Inertial Assistance

Recently,with the development of GNSS and the construction China Beidou Satellite Navigation system,satellite based positioning technology has been developing day by day from initial birth to mature.The demand for satellite navigation technology has gained an obvious increasing.The GNSS can provide all-weather real-time positioning and navigation service.However,it cannot provide stable and reliable navigation information in complex environments,such as high dynamics and weak signals.In order to furtherly enhance the performance of satellite navigation,using inertial information to assist GNSS has become a research hotspot in the community.Based on a national defense key pre-research project,this paper carried out the research on Inertial Assisted Satellite Positioning Control Technology,the major contents could be summarized as follows:(1)This paper researched the baseband signal processing technology in BDS/GPS receiver.According to the mechanism and principles of satellite signals generation,an FPGA based BDS/GPS baseband signal processor was designed.The specifications of the implementation and functional simulation were reveasled,and the experiments were conducted to verify each module of the baseband processor are introduced in detail.(2)The inertial information assisted BDS/GPS singnal tracking loop was studied in this paper.For complex environments,such as high dynamics and weak signals,the conventional signal tracking loop couldnot continuously track satellite signals stably.Signal acquisition and tracking technology of inertial information-aided receiver were designed to improve the ability of the receiver to acquire and track satellite signals in complex environments.In addition,for shortening the cold start time,this paper designed an inertial assisted fast hot start method,which greatly decreased the initial positioning time.(3)This paper carried out a research on BDS/GPS dual-constellation positioning fusion technology.A dual-constellation fusion positioning algorithm was designed for the difference of dual-constellation system positioning algorithm.Aiming at the problem of coarse and cluttered positioning results of traditional positioning algorithm,an Unscented Kalman Filter(UKF)navigation solutions determination algorithm was designed.Based on this,an adaptive correction factor was introduced to enhance the positioning accuracy and robust performance of the system.Finally,the hardware and software design of the inertial satellite positioning control system was introduced in detail.The overall navigation performance of the system was verified by simulator test and sports car test.