A Method of Inertial-Astronomical Integrated Navigation for Deep Space Exploration Vehicle

Abstract

The present invention provides an inertial-astronomical integrated navigation method for deep space exploration aircraft, comprising steps: S1, establishing a heliocentric inertial coordinate system, establishing a heliocentric orbital coordinate system, and calculating the position of the aircraft relative to the sun at the heliocentric position based on the angle measured by an optical sensor The direction vector of the inertial system; S2, calculate the direction vector of the earth relative to the sun in the heliocentric inertial system; S3, according to the inertial navigation measurement results, solve the direction vector of the aircraft relative to the earth center in the heliocentric inertial system; S4, calculate the direction vector of the aircraft relative to the sun in the heliocentric inertial system; The direction vector of the heliocentric inertial system; S5, based on the direction vector error, using PI filter to estimate the position / velocity error correction; S6, based on the position / velocity error correction inertia-astronomical integrated navigation. The inertial-astronomical integrated navigation method of the deep space exploration aircraft of the present invention can suppress the cumulative error of the inertial navigation when the aircraft is navigating in orbit in real time.

Description

technical field [0001] The invention relates to the technical field of deep space astronomical navigation, in particular to an inertial-astronomical combined navigation method for a deep space exploration aircraft based on a star sensor and an optical sensor, which is used for on-orbit real-time navigation of the aircraft. Background technique [0002] Because the existing earth satellites and lunar exploration vehicles are closer to the earth, the ground measurement and control delay is shorter, and more sensors are available for the establishment of the ground measurement and control link, and the reliability of ground orbit determination is high. The deep space exploration aircraft is far away from the earth, and the ground measurement and control delay is sometimes as long as 30 minutes. The ground measurement orbit requires a reliable device-ground measurement and control link. of establishment. [0003] During the in-orbit operation of the aircraft, not only the attit...

AI Technical Summary

Problems solved by technology

However, GNSS compatible machines and magnetometers are not available for deep space exploration; pulsar-based navigation requires complex and expensive pulsar sensors

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