An autonomous celestial navigation method based on solar oscillation time delay

Abstract

The invention relates to an autonomous celestial navigation method based on sun shock time delay. The autonomous celestial navigation method comprises the following steps: with the acute change of a central wavelength of a sun spectral line caused by sun shock as a feature, respectively recording a moment that the feature is directly received by an atomic frequency discriminator facing towards the sun and a moment that the feature is reflected by a reflecting celestial body and is received by the atomic frequency discriminator facing towards the reflecting celestial body, so as to obtain time delay quantity, and providing navigation information of a space vehicle; and establishing a state model of the space vehicle according to orbital dynamics, establishing an implicit expression measurement model including a non-linear equation according to the sun shock time delay, and estimating the position and speed of the space vehicle by virtue of an implicit expression traceless Kalman filter utilizing a dichotomy. The autonomous celestial navigation method belongs to the autonomous navigation field of the space vehicles and is applicable to the navigation and location of transfer orbits or surrounding orbits for planetary exploration in the solar system.

Description

technical field [0001] The invention belongs to the field of autonomous navigation of spacecraft, and relates to an astronomical navigation method for providing position information of a spacecraft by using spectral wavelength changes caused by solar oscillations as a feature, and is suitable for navigation and positioning of planetary detection transfer orbits or circumnavigation orbits in the solar system. Background technique [0002] For deep space exploration missions, the guidance and control of spacecraft needs to rely on navigation information, and navigation accuracy has an important impact on the success or failure of missions. Navigation is to obtain the position and velocity information of the spacecraft and determine the orbital parameters. [0003] At present, navigation information is generally provided for spacecraft through ground measurement and control stations. However, as the distance between the spacecraft and the earth increases, the round-trip delay ...

AI Technical Summary

Problems solved by technology

[0005] The technical problem to be solved by the present invention is: in order to make up for the deficiencies of the existing astronomical navigation methods, a method for measuring the time delay of spacecraft navigation information provided by the wavelength variation characteristics caused by solar oscillations is proposed, and a hidden dichotomy method is proposed. The unscented Kalman filter solves the problem that the measurement model is implicit and contains nonlinear equations, and provides real-time, high-precision autonomous navigation information for spacecraft in transfer orbits or orbits

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