MEMS (micro-electromechanical system) pressure sensor-based collaborative satellite positioning method and system

Abstract

The invention discloses an MEMS (micro-electromechanical system) pressure sensor-based collaborative satellite positioning method and system. The method comprises the following steps that: a navigator obtains the satellite instantaneous geocentric coordinates of four satellites through using ephemeris broadcasted by the satellites, and the navigator, based on the conversion relationship of geocentric coordinates and geodetic coordinates, builds a pseudorange observation equation corresponding to each of the four satellites through using the pseudorange observation quantities of the satellites with the geodetic coordinate system of the navigator adopted as a solving objective; geodetic coordinate-based height information is obtained based on an MEMS pressure sensor, and an elevation information constraint equation is established based on the height information; and the current geodetic coordinate solving model of the navigator is formed based on the pseudorange observation equation and the elevation information constraint equation, and the geocentric coordinates of the navigator are obtained based on the conversion relationship of the geocentric coordinates and the geodetic coordinates. According to the MEMS (micro-electromechanical system) pressure sensor-based collaborative satellite positioning method and system provided by the embodiments of the invention, the MEMS pressure sensor and the satellite signals are combined to perform positioning, and therefore, a collaborative positioning function is realized under a condition that satellite signal difference or only four satellites exist.

Description

technical field [0001] The invention relates to the technical field of satellite navigation, in particular to a method and system for coordinating satellite positioning based on MEMS pressure sensors. Background technique [0002] The existing satellite positioning system receives satellite signals through a navigator, first uses the ephemeris broadcast by satellites to calculate the exact position coordinates of each satellite, and then uses the pseudo-range observations of the satellites to establish ρ to establish the pseudo-range observation equation (1), Because there is a clock error in the receiver, it is necessary to take the receiver clock error as an unknown and solve it together with the receiver position coordinates (X, Y, Z) on the navigator. [0003] [0004] Among them, (X i , Y i ,Z i ) is the instantaneous geocentric coordinates of the satellite obtained from the satellite ephemeris, (X, Y, Z) is the geocentric coordinates of the receiver to be obtaine...

AI Technical Summary

Problems solved by technology

The MEMS pressure sensor can calculate the elevation dimension information with a certain precision, which can provide users with accur

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