Deep space exploration aircraft inertia-astronomical integrated navigation method

Abstract

The invention provides a deep space exploration aircraft inertia-astronomical integrated navigation method which comprises the following steps: S1, establishing a heliocentric inertial coordinate system, establishing a heliocentric orbit coordinate system, and calculating a direction vector of an aircraft relative to the sun in the heliocentric inertial system based on an angle measured by an optical sensor; S2, calculating a direction vector of the earth relative to the sun in a heliocentric inertial system; S3, resolving a direction vector of the aircraft relative to the earth center in theheliocentric inertial system according to the inertial navigation measurement result; S4, calculating the direction vector of the aircraft relative to the sun in the heliocentric inertial system; S5,estimating a position / speed error correction amount by adopting PI filtering based on the direction vector error; and S6, performing inertial-astronomical integrated navigation based on the position / speed error correction amount. According to the deep space exploration aircraft inertia-astronomical integrated navigation method, inertial navigation accumulative errors can be inhibited when the aircraft performs on-orbit real-time navigation.

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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