Satellite attitude orbit determining system and method

Abstract

The invention provides a satellite attitude orbit determining system and a satellite attitude orbit determining method. The method comprises the following steps of: acquiring a pseudo-range, a pseudo-range rate and a carrier phase data from satellite navigation signals from an attitude orbit acquisition module by an attitude orbit determining module in an on-satellite subsystem, generating inter-satellite relative position information, inter-satellite relative velocity information and three-dimensional position information by using the pseudo-range, the pseudo-range rate and the carrier phase data, performing a federal filtering algorithm on the three-dimensional position information and a satellite starlight elevation to generate position information and velocity information of a relative satellite inertia system, performing joint attitude determining by using the satellite navigation signals, the satellite attitude angle information and the satellite starlight elevation to generate a triaxial angle, and performing optimal estimation on the triaxial angle to acquire a triaxial attitude angle and a triaxial attitude angular velocity of a satellite; and performing orbital transfer and attitude adjusting control by an attitude orbit control computer according to the information output by the attitude orbit determining module. By adopting the system and the method, the attitude determining precision and the orbit determining instantaneity can be improved.

Description

technical field [0001] The invention relates to the field of aircraft design, in particular to a satellite attitude orbit determination system and method. Background technique [0002] figure 1 It is a schematic diagram of the structure of the existing satellite attitude orbit determination system. Combine now figure 1 , to describe the existing satellite attitude orbit determination system, specifically as follows: [0003] The existing satellite attitude and orbit determination system includes an on-board subsystem 10 and a ground subsystem 11 . Among them, the on-board subsystem 10 is used to obtain the data for determining the satellite orbit and determining the satellite attitude, complete the attitude determination of the satellite according to the data for determining the satellite attitude, and downlink the data for determining the satellite orbit to the ground subsystem 11; System 11 performs orbit determination calculations based on the existing flight dynamics...

AI Technical Summary

Problems solved by technology

[0005] To sum up, in the existing satellite attitude and orbit determination system, the orbit determination result needs to depend on the distance between the satellite and the ground, and the orbit determination operation process completes the complex mathematical operation process for the ground subsystem. In order to improve the orbit determination accuracy, it is necessary to It takes a long calculation cycle; the accuracy of attitude determination using inertial devices alone is not high and needs to be further improved; once the ground subsystem participates in satellite orbit determination, the real-time performance of orbit determination cannot be guaranteed

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