Independent celestial navigation method for Mars capturing section of deep space probe

Abstract

The invention relates to an independent celestial navigation method for a Mars capturing section of a deep space probe. The method comprises the following steps of: establishing a state model of the deep space probe according to a circular restrictive four-body track dynamics model; acquiring picture element and picture line information of Mars, Martian satellites and a background fixed star, converting the acquired picture element and picture line information into angle information of the Mars, the Martian satellites and the background fixed star and establishing an angle measuring model of the Mars, a Martian satellite I and a Martian satellite II; and estimating the attitude information of the probe by adopting a q-method and estimating the position and speed of the deep space probe in combination with Unscented Kallman filtering. The method has high estimation accuracy, and is very suitable for independent navigation of Mars capturing. The method belongs to the technical field of aerospace navigation. By adopting the method, high-accuracy navigation parameters can be provided for Mars capturing of the deep space probe, and references can be provided for the design of an independent navigation system of the deep space probe.

Description

technical field [0001] The invention relates to an autonomous astronomical navigation method based on the angle information of Mars, Phobos and Deimos when a deep space probe is in the Mars capture stage, and is an autonomous navigation method very suitable for the Mars capture stage. Background technique [0002] During the flight of the deep space probe, the navigation accuracy of the Mars capture segment of the probe directly affects the next stage of exploration tasks, such as the accuracy of the Mars capture and landing, and the navigation accuracy of the flight by force. If the navigation error at this stage is too large If the orbit control propulsion system is too large, the orbit of the probe cannot be adjusted in time through the orbit control propulsion system. After the opportunity of orbit control is missed, it cannot be adjusted back to the predetermined orbit, and it cannot be captured by Mars or the orbit seriously deviates from the predetermined orbit after t...

AI Technical Summary

Problems solved by technology

[0005] The technical problem to be solved by the present invention is: to overcome the disadvantages of asteroid and pulsar-based autonomous navigation methods such as the small number of navigation asteroids or navigation pulsars, low precision, and high requirements for detector orbit design, and to make up for the traditional observation of Mars and Phobos. The lack of pixel image line information in the methods of Deimos and Deimos is constrained by the attitude of the probe, which provides a high-precision autonomous astronomical navigation method for deep space probes in the process of capturing Mars

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